Only the online system has current version.
Verify copy against the online system before use.
PACKAGING AND
TRANSPORTABILITY MANUAL
MILITARY AIRCRAFT SYSTEMS DIVISION
P-2048.doc 09/03/97 7:17 AM
SPECIFICATION NO.
P-2048
PAGE
1
PACKAGING SPECIFICATION
SPECIFICATION TITLE
PREPARATION FOR DELIVERY OF SF18DFTS1 CENTER/AFT FUSELAGE
ASSEMBLY, FATIGUE TEST ARTICLE COMPONENTS ASSEMBLY,
BY AIR; AND PRESERVATION FOR STORAGE, AND DEPRESERVATION
FOR PRODUCTION, IN SWITZERLAND
REV
of
11
—
EFFECTIVE
4 October 1995
RELEASE DOCUMENT
EO F55352
SUPERSEDES
None
1.0
SCOPE
1.1
PURPOSE AND APPLICATION
This specification establishes the requirements for preservation for long-term storage, depreservation for
production, and requirements for packaging, packing, loading, and unloading for the SF18DFTS1
center/aft fuselage assembly (ctr/aft fus assy) when transported on the PK-21550 shipping fixture, by air.
1.2
This specification applies to shipments from Northrop Grumman, El Segundo, California to F+W,
Switzerland, in accordance with the requirements specified in (TBE) Northrop Grumman
Transportability Report. This specification will apply to SF18DFTS1 center/aft fuselage assembly,
fatigue test article components assembly only.
2.0
APPLICABLE DOCUMENTS
2.1
The following documents form a part of this specification to the extent specified herein.
2.2
Military
2.2.1
MIL-P-116
Preservation, Methods of
2.2.2
MIL-B-117
Bags, Sleeves, and Tubing-Interior Packaging
2.2.3
MIL-B-121
Barrier Material, Greaseproofed, Waterproofed, Flexible
2.2.4
L-P-378
Plastic Sheet and Strip, Thin Gauge, Polyolefin
2.2.5
PPP-C-795
Cushioning Material, Flexible, Cellular, Plastic Film, for Packaging Application
2.2.6
MIL-STD-2073
DoD Material Procedures for Development and Application of Packaging
Requirements
2.2.7
MIL-C-16173
Corrosion Preventive Compound, Solvent Cutback, Cold Application
2.2.8
MIL-T-43435
Tape, Lacing, and Tying
2.3
Military Aircraft Systems Division
2.3.1
PK-21550
Shipping Fixture – F/A-18 Ctr/Aft Fus Assy, Swiss
2.3.2
SK-18-0003
Protective Cover – F/A-18 Ctr/Aft Fus Assy, Swiss
PACKAGING &
TRANSPORTABILITY
MANUAL
P-2048.doc 09/03/97 7:17 AM
PAGE
2 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
2.4
MDA
2.4.1
MD-11
Pressure-Sensitive Tape
2.4.2
74A900000
Finish Specification for F/A-18 Aircraft
2.4.3
P.S. 12010
Cleaning, Solvent, Hand or Immersion
2.4.4
P.S. 13204
Conversion Coating (Brush and Spray Treatment)
2.4.5
P.S. 13630
Painting of F/A-18 and A/V-8 Aircraft
2.4.6
P.S. 20001
(EO F86350)
Protection of Parts During Fabrication and Temporary Storage
2.5
Commercial
2.5.1
Plastic Edge-Pak, #8PLA
2.6
Addendum
P-2048
The following documents are furnished for reference purposes only; they are current at the time of
release and will not be updated.
2.6.1
PS12010
Cleaning, Solvent, Hand or Immersion
2.6.2
PS13204
Conversion Coating (Brush or Spray Treatment)
2.6.3
PS13630
Painting of F/A-18 and A/V-8 Aircraft
2.6.4
PS20001
EO F86350
Protection of Parts During Fabrication and Temporary Storage
3.0
REQUIREMENTS
The requirements of this document apply to the complete center/aft fuselage assembly, less Swiss incountry work content. The center/aft fuselage assembly will be secured on PK-21550 shipping fixture.
Cost Center 2010 completion kits and SMI ancillary parts that are to be stored in Switzerland longer
than 6 months will be preserved to level A, packing to level B, in accordance with MIL-STD-2073.
Shipping fixture, PK-21550 (Fig. 1) has been designed to load into L-100-30 freighter aircraft. This
fixture will be provided as customer furnished equipment (CFE) by the Swiss government.
Ground rules/assumptions for long-term storage:
a.
The center/aft fuselage shall be stored in Switzerland for 30 months before final assembly, in a
controlled environment 40°F – 80°F, 30% – 70% relative humidity, or better.
b.
No cyclical maintenance shall be required while in storage.
c.
For post-storage inspection, all materials and equipment shall be supplied by the Swiss.
d.
All materials and equipment required for depreservation for production shall be supplied by the
Swiss.
3.1
Preservation/Packaging/Packing
3.1.1
Openings in Fuselage
3.1.1.1
Openings in fuselage created by the omission of doors, covers, and/or vertical stabilizers shall be
covered with a minimum of one layer of MIL-B-121, Type 1, Grade A, waterproof paper, secured in
place with 2-inch wide MD-11, No. 1 tape, 3M #231. Cover to extend a minimum of 1 inch beyond
open space or fastener pattern, whichever is greater.
3.1.1.2
Plastic Edg-Pak, #8 PLA shall be installed on the edge of fuselage skins at forward end of center
fuselage.
3.1.2
Miscellaneous
PACKAGING &
TRANSPORTABILITY
MANUAL
P-2048.doc 09/03/97 7:17 AM
3.1.2.1
PAGE
REVISION SPECIFICATION
LETTER
NUMBER
3 of 11
—
P-2048
Electrical cables, wires, and wire harnesses shall be coiled and taped a minimum of three places,
cushioned to prevent abrasion, and secured to aircraft structure with 2-inch wide MD-11, No. 1 tape,
3M #231. Ties made with polyester lacing tape meeting the requirements of MIL-T-43435, Type II,
Finish C may be used in lieu of tape for all bundling and securing requirements herein.
CAUTION:
Minimum bend radius of wires shall be six times outside diameter (OD) of wire.
Minimum bend radius of cables or bundles shall be 10 times OD of cable or bundle.
3.1.2.2
Electrical cables, wires, and wire harnesses impractical to coil shall be taped as required, cushioned to
prevent abrasion, and secured to the structure with MD-11, No. 1 tape, 3M #231.
3.1.2.3
Unmated connectors on cables, wires, and wire harnesses shall be protected per paragraph 6.14 of
P.S. 20001 (see Addendum, para. 2.6.4). Electrical bond lugs, studs, and bare wire ends shall not
be covered.
NOTE: All bare unconnected electrical wires are extra length and are to be trimmed to length at next
assembly. Corrosion protection of ends is not required.
3.1.3
BARE METAL
Bare metal bolts and bushings, and unpainted metal surfaces other than mold line skin surfaces shall be
preserved per paragraph 6.15 of P.S. 20001 (see Addendum, para. 2.6.4) and wrapped or covered with
greaseproofed paper, MIL-B-121, Grade “A.” Secure wrap or cover with MD-11, No.1 tape, 3M #231.
3.1.3.1
Protect OML surfaces per paragraph 6.12 and 6.13 of P.S. 20001 (see Addendum, para. 2.6.4).
3.2
Mounting SF-18 Ctr/Aft Fus Assy in Shipping Fixture PK-21550 (HFPR 74A0000l0-5103)
(Fig. 2)
Attach overhead crane to strongback (HFLA74A000010-5001). Align the strongback in position and
lower it over center/aft fuselage. Connect strongback to forward and aft hoist points of the fuselage.
CAUTION:
The attach point (overhead crane to strongback) for lifting the strongback only and for
lifting the strongback with center/aft fuselage are not the same. Check attach points
between overhead crane and strongback for every lift operation to avoid mishap.
3.2.1
Attach fittings (PK-21550-85) to fuselage wing bulkhead Y488.000 prior to attachment of overhead
hoist to strongback, for removal of center/aft fuselage from NORAIL.
3.2.1.1
Parts required (numbers in parentheses are for attaching on (1) -85 fitting only:
Fitting
PK-21550-85 (1)
Bushing
PK-21550-323 (2)
Pin
PK-21550-313 (1)
Bolt
PK-21550-327 (1)
Sleeve
PK-21550-317 (2)
Nut
PK-21550-329 (1)
Washer
PK-21550-321 (2)
Pin-Cotter
PK-21550-381 (1)
3.1.1.2
Assemble two sleeves (PK-21550-317) into lower lug of wing bulkhead Y488.000, inserting one from
each side.
3.2.1.3
Check to ensure that sleeves (-317) are touching approximately at center of -313 pin. Assemble fitting
(PK-21550-85) to bulkhead, align holes in -85 fitting with lower bulkhead lug hole, and slide pin
(PK-21550-313) through -85 fitting and bulkhead.
3.2.1.4
Place a fiber washer (PK-21550-321) under each bushing (PK-21550-323) prior to inserting a bushing
into each end of pin (-313).
PACKAGING &
TRANSPORTABILITY
MANUAL
P-2048.doc 09/03/97 7:17 AM
PAGE
4 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
3.2.1.5
Feed bolt (PK-21550-327) through assembly of pin and bushings. Attach nut (PK-21550-329) and
HAND TIGHTEN ONLY (see -81 torque plate, Fig. 3). Insert cotter pin (PK-21550-381) and spread
split end to avoid accidental removal.
3.2.2
Follow instructions in paragraphs 3.2.1.1 through 3.2.1.5 for assembly of second -85 fitting to
corresponding bulkhead lug hole.
3.2.3
Attach bar (PK-21550-91) to fuselage arresting hook lugs before removal of fuselage from NORAIL.
3.2.3.1
Parts required:
Tie Bar
PK-21550-91 (1)
Nut
PK-21550-365 (1)
Sleeve
PK-21550-319 (4)
Washer Csk
PK-21550-371 (1)
Pin
PK-21550-351 (1)
Washer Plain
PK-21550-377 (1)
Washer
PK-21550-379 (1)
Pin-Cotter
PK-21550-383 (1)
Bolt
PK-21550-357 (1)
Bolt
PK-21550-359 (1)
3.2.3.2
Slip two flanged sleeves (-319) into each fuselage arresting hook lug hole for the inboard/outboard faces.
3.2.3.3
Insert the sleeve end of the tie bar (-91) between the flange faces of bushings (-319).
CAUTION: Take care to avoid contacting the arresting hook lugs of adjacent surfaces with the (-91)
tie bar end.
3.2.3.4
Slip the pin (-351) through arrester hook lugs and tie bar sleeve end. Align holes in pin and sleeve and
insert bolt (-357) with csk washer (-371) under the head.
3.2.3.5
Assemble plain washer (-377) and nut (-365), HAND TIGHTEN ONLY. Insert cotter pin (-383) and
spread split end to avoid accidental removal.
3.2.4
Clear immediate loading area prior to lowering fuselage into fixture.
3.2.5
Inspect the fuselage to ensure that all doors and access panels are closed and secured, all holes and
openings are covered, and all protruding hardware, cables, etc., are protected as specified herein.
3.2.6
Inspect shipping fixture (PK-21550) to ensure that the surfaces are clear of tools or other loose materials,
and that attach fitting and mating surfaces are clean and dry.
3.3
Attaching Fuselage to Fixture
3.3.1
Lower the fuselage over the fixture, adjusting as necessary to align the fittings with their respective
mating surfaces. Hanging end of the tie bar fitting (-91) must be held toward the rear and may be used to
guide the pin (-351) into the aft fitting locating lugs (PK-21550-87) on the fixture.
CAUTION:
The fuselage weight must be supported from overhead with strongback
HFLA74A000010-5001 until the pin (-351) is fully seated and the screw end of the bar (91) anchored at fitting (PK-21550-89) with stated torque applied to bolt (PK-21550-359)
(Fig. 3).
3.3.1.1
When the pin (-351) is directly opposite the open side of fitting (-87) lugs, the fuselage should be moved
aft until the pin (-351) is fully engaged in the lugs.
3.3.1.2
The 1-1/4 inch diameter bolt (-359) with lock washer (-379) under the head must be fed into screw end
of tie bar and tightened with torque of 6500–8000 inch-pounds (542–665 foot-pounds) (see torque
plate -79, Fig. 3). Note that a cross bar is located on forward edge of fitting (-89) to assist in centering
tie bar for bolt.
P-2048.doc 09/03/97 7:17 AM
3.3.1.3
PACKAGING &
TRANSPORTABILITY
MANUAL
PAGE
5 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
Carefully lower fuselage until wing lug fittings (-85) rest flush on fixture plates (PK-21550-55). (It may
be necessary to shim between fittings (-85) and fixture plates (-55). Maintain tension on overhead hoist
cables until wing bulkhead fitting bolts (PK-21550-13) are installed.
CAUTION:
The wing bulkhead fittings (-85) are free to rotate and will not support a load until
secured to the fixture plates (-55). The fuselage will rotate forward about the aft fitting
pin (Fig. 3 and 4).
3.3.1.4
Insert bolts (PK-21550-13) with csk washers (-369) under the heads. Assemble plain washers (-375)
(Fig. 3). Insert cotter pins (-381) and spread split end to avoid accidental removal.
3.3.1.5
Inspect attach fittings to ensure that all items have been installed correctly, torque values applied to
bolts, and cotter pins are in place and secured. The aircraft weight must now be gradually transferred to
the fittings, and strongback released from the fuselage hoist points.
3.4
Environmental Protection of Ctr/Aft Fus Assy During Transportation
3.4.1
Place segments of the reusable plastic tarpaulin (SK-18-0003) over center/aft fuselage assembly,
mounted on the shipping fixture, and secure.
3.5
Loading Trailer for Transport to Airport
3.5.1
The weight of the center/aft fuselage assembly and shipping fixture combined is approximately
7,395 pounds. For transporting mounted fuselage assembly to trailer loading area, a forklift capable of
moving loads of 10,000 pounds or greater, on 60-inch load centers is required, with forks a minimum of
72 inches in length (96 inches preferred).
3.5.2
Care must be exercised when running forks into shipping fixture slots to avoid forklift contact with any
part of the center/aft fuselage assembly (leading edge extension which protrudes just forward of the wing
attach bulkheads).
3.5.3
Transport center/aft fuselage assembly to trailer loading area and place on trailer bed.
3.5.4
Sections of wooden 2 × 4s, or equivalent, may have to be placed between the skids of the shipping
fixture and trailer bed to compensate for crown of trailer bed.
3.5.5
Driver of tractor-trailer will secure shipping fixture to trailer bed and transport to airport.
3.6
Loading the Ctr/Aft Fus Assy into the Freighter Aircraft
3.6.1
The tractor-trailer driver will position the trailer in line with the loading ramp of the freighter aircraft,
following the directions of the aircraft’s loadmaster.
3.6.2
The tractor-trailer driver will release the center/aft fuselage assembly, mounted on the shipping fixture,
from the trailer bed, removing any 2 × 4s, or equivalent, that might have been used.
3.6.3
The aircraft’s loadmaster will direct the transfer of the center/aft fuselage assembly from the trailer into
the aircraft and secure it.
3.6.4
The L-100-30 freighter aircraft can carry a maximum of two center/aft fuselage assemblies mounted on
shipping fixtures.
3.7
Unloading the Ctr/Aft Fus Assy From the Freighter Aircraft
3.7.1
The aircraft’s loadmaster will direct the transfer of the center/aft fuselage assembly from the aircraft onto
a trailer bed, in Switzerland.
3.7.2
The tractor-trailer driver will secure the center/aft fuselage assembly mounted on the shipping fixture to
the trailer bed.
3.7.3
Transport center/aft fuselage assembly to unloading area in F + W factory.
3.7.4
Remove segments of the reusable plastic tarpaulin (SK-18-0003) from the center/aft fuselage assembly.
3.7.5
Check center/aft fuselage assembly for damage. Record any damage with an independent Cargo
Surveyor’s Report and photographs.
PACKAGING &
TRANSPORTABILITY
MANUAL
P-2048.doc 09/03/97 7:17 AM
PAGE
6 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
3.7.6
Remove center/aft fuselage assembly, on shipping fixture, from trailer bed and place on floor.
3.8
Detachment of Ctr/Aft Fus Assy From Shipping Fixture
3.8.1
Attach a sling to fuselage hoist points and take up slack in lines to permit removal of attach hardware.
Release the wing bulkhead fittings (-85) from fixture plates (-55) first, as shown in (Fig. 3).
CAUTION:
Do not attempt to remove the (-85) fittings from the bulkhead before detaching them
from the (-55) fixture plates.
Four guideropes must be attached to the four corners (extremities) of the fuselage for control while it is
suspended.
3.8.2
Release the 1-1/4 inch diameter bolt at the rear fitting (-89) and allow the fuselage to move forward
enough to release the pin (-351) from the open lugs in (-87) fitting.
3.8.3
Check to make certain the fixture is clear of obstructions and that there are no cables, etc., that may
become entangled during lifting. Raise the center/aft fuselage assembly from the shipping fixture. The
fuselage may be moved aside before fittings are detached from wing bulkhead and arresting hook.
3.8.4
Remove the following attaching hardware from center/aft fuselage bulkhead fitting (-85), pin (-313),
sleeve (-317), and bushing (-323). These items shall be reassembled and reattached to fixture plates
(-55) for return to Northrop Grumman. The tie-bar fitting (-91) shall be removed from the arresting
hook lugs, along with the flanged sleeves (-319). The openings left by the removal of the attach
hardware shall have caps placed over them.
3.8.5
The tie-bar (-91) and pin (-351) with sleeve (-319) shall be assembled into the fixtures fittings (-87 and
-89). Bolt (-359) and washer (-379) assembled and hand tightened to retain the tie-bar.
3.8.6
Return shipping fixture and reusable protective covers to Northrop Grumman, El Segundo, CA for future
shipments.
3.8.7
While in storage, a plastic shroud will be draped over the center/aft fuselage assembly to act as a dust
cover.
3.9
Post-Storage Inspection
3.9.1
Corrosion Inspection
The protection measures applied prior to long-term storage will protect aircraft components from most
corrosion; however, some superficial corrosion may occur. All external surfaces, bays, access doors,
etc., shall be opened and thoroughly inspected prior to final assembly. The following information details
how to detect and remove any corrosion that may occur.
3.9.1.1
Aluminum Alloys
The aluminum alloys are susceptible to pitting and intergranular corrosion. The corrosion product
appears as a white or gray powdery substance. It can be removed using abrasive sheet, 320- grit or finer
conforming to P-C-451 or equivalent. After the corrosion is removed, the bare surface should be
protected with chemical conversion coating per PS 13204 (see Addendum, para. 2.6.2).
3.9.1.2
Corrosion Resistant Steels
Stainless steel components will generally be used for attaching hardware such as screens, bolts, washers,
clamps, and brackets. These alloys are considered corrosion resistant, but are prone to pitting. The pits
will appear as a red, brown, or black stain. The corrosion product can be removed by the use of abrasive
mat, MIL-A-9962, Type 1, Grade B. The cleaning residue can be wiped up with a solvent-soaked clean
cheese cloth.
P-2048.doc 09/03/97 7:17 AM
3.9.1.3
PACKAGING &
TRANSPORTABILITY
MANUAL
PAGE
7 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
Cadmium
Cadmium plate is used to protect low alloy and carbon steel parts such as washers, bolts, and screws.
Corrosion will appear as white, brown, or black mottling on the surface. This is evidence of the normal
cathodic protection of the steel. The cadmium plate on the steel is still protecting the steel until signs of
red rust appear on the underlying metal. If evidence of rust occurs, the hardware should be removed and
replaced.
3.9.1.4
OML
The entire OML of the aircraft should be inspected for evidence of blistering, peeling, or other sign of
corrosion. If evidence of corrosion appears, remove the corrosion and reapply the primer in accordance
with PS 13630 (see Addendum, para. 2.6.3).
3.10
Depreservation for Production
3.10.1
Tape residue, protective coatings, grease, etc., shall be removed per PS12010 (see Addendum
para. 2.6.1).
4.0
PRODUCT QUALITY
4.1
Product Quality shall verify that the materials, tools, equipment, and procedures for
preservation/packaging/packing of the center/aft fuselage assembly and the installation of the fuselage
assembly into the shipping fixture are as specified herein.
5.0
PREPARATION FOR DELIVERY
5.1
This section is not applicable to this specification.
6.0
NOTES
6.1
Information pertaining to, or additional copies of this document may be obtained from:
Northrop Grumman Corporation
Military Aircraft Systems Division
Support Equipment and Transportability Engineering
Orgn. 7E80/W2
One Hornet Way
El Segundo, CA 90245-2804
P-2048.doc 09/03/97 7:17 AM
PACKAGING &
TRANSPORTABILITY
MANUAL
FIGURE 1
PAGE
8 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
P-2048.doc 09/03/97 7:17 AM
PACKAGING &
TRANSPORTABILITY
MANUAL
FIGURE 2
PAGE
9 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
P-2048.doc 09/03/97 7:17 AM
PACKAGING &
TRANSPORTABILITY
MANUAL
FIGURE 3
PAGE
10 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048
P-2048.doc 09/03/97 7:17 AM
PACKAGING &
TRANSPORTABILITY
MANUAL
FIGURE 4
PAGE
11 of 11
REVISION SPECIFICATION
LETTER
NUMBER
—
P-2048