[Federal Register Volume 68, Number 246 (Tuesday, December 23, 2003)]
[Rules and Regulations]
[Pages 74167-74169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31195]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-180-AD; Amendment 39-13394; AD 2003-25-11]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 
747SP Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing airplane models, that requires a one-time 
inspection to identify all H-11 steel bolts installed in the latch 
fittings of the cargo doors, repetitive inspections for cracked or 
broken H-11 steel bolts, and follow-on and corrective actions if 
necessary. This amendment also requires eventual replacement of all H-
11 steel bolts in the latch fittings of the cargo doors with Inconel 
bolts. This action is necessary to prevent broken bolts in the latch 
fittings, which could reduce the capability of the door latch to keep 
the door closed, and result in loss of a cargo door and consequent 
rapid depressurization of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective January 27, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 27, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to

[[Page 74168]]

include an airworthiness directive (AD) that is applicable to certain 
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747SR, and 747SP series airplanes was published 
in the Federal Register on August 27, 2003 (68 FR 51521). That action 
proposed to require a one-time inspection to identify all H-11 steel 
bolts installed in the latch fittings of the cargo doors, repetitive 
inspections for cracked or broken H-11 steel bolts, and follow-on and 
corrective actions if necessary. That action also proposed to require 
eventual replacement of all H-11 steel bolts in the latch fittings of 
the cargo doors with Inconel bolts.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 566 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 179 airplanes of U.S. registry 
will be affected by this AD, that it will take between 2 and 8 work 
hours per airplane (depending on the airplane's configuration) to 
accomplish the required inspection, and that the average labor rate is 
$65 per work hour. Based on these figures, the cost impact of the AD on 
U.S. operators is estimated to be between $130 and $520 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-25-11 Boeing: Amendment 39-13394. Docket 2001-NM-180-AD.

    Applicability: Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series 
airplanes; line numbers 1 through 721 inclusive, 976, and 982; 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent bolts from breaking in the latch fittings of the 
cargo doors, which could reduce the capability of the door latch to 
keep the door closed, and result in loss of a cargo door and 
consequent rapid depressurization of the airplane, accomplish the 
following:

Service Bulletin References

    (a) The following information pertains to the service bulletin 
referenced in this AD:
    (1) The term ``service bulletin'' as used in this AD, means the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2464, 
Revision 1, dated August 30, 2001.
    (2) Although the service bulletin referenced in this AD 
specifies to submit certain information to the manufacturer, this AD 
does not include such a requirement.
    (3) Although the service bulletin specifies that the actions 
therein must be accomplished prior to or concurrently with the 
actions in Boeing Alert Service Bulletin 747-52A2167 and Boeing 
Service Bulletin 747-52-2197, this AD does not include such a 
requirement. AD 80-14-11, amendment 39-3831, already requires 
accomplishment of Boeing Alert Service Bulletin 747-52A2167, 
Revision 1, dated March 28, 1980.
    (4) Inspections and replacements accomplished before the 
effective date of this AD per Boeing Alert Service Bulletin 747-
53A2464, dated March 15, 2001, are considered acceptable for 
compliance with this AD.

Initial Inspection

    (b) Within 1 year after the effective date of this AD: Do a one-
time detailed inspection to identify all H-11 steel bolts installed 
in the latch fittings of the main deck side cargo door, nose cargo 
door, and the forward and aft lower lobe cargo doors, as applicable. 
Do the inspection by checking the bolt part number stamped on the 
bolt head, or verifying the bolt is steel by using a magnet, per the 
service bulletin. If no H-11 steel bolt is found, no further action 
is required by this paragraph. If any H-11 steel bolt is found, do 
the requirements of paragraph (c) of this AD.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Follow-On Inspections/Corrective Actions

    (c) For any H-11 steel bolt found during any inspection required 
by paragraph (b) of this AD: Before further flight, do an ultrasonic 
inspection for cracked or broken bolts, or replace the H-11 steel 
bolt with an Inconel bolt, per the service bulletin. Replace any 
cracked or broken bolt with an Inconel bolt before further flight 
per the service bulletin. Repeat the ultrasonic inspection of 
remaining H-11 steel bolts in the latch fittings of the main deck 
side cargo door, nose cargo door, and the forward and aft lower lobe 
cargo doors, at intervals not to exceed 18 months until the 
terminating action required by paragraph (d) of this AD is done.

Terminating Action

    (d) Within 6 years after the effective date of this AD: Replace, 
with Inconel bolts, all H-11 steel bolts in the latch fittings of 
the main deck side cargo door, nose cargo door, and the forward and 
aft lower lobe cargo doors, per the service bulletin. The procedures 
for this replacement include

[[Page 74169]]

performing a detailed inspection of the bolt hole for corrosion; 
oversizing the bolt hole to remove any corrosion; installing a new 
bolt, nut, and washers; and applying sealant. Such replacement 
terminates the repetitive inspections required by paragraph (c) of 
this AD. If corrosion is found and oversizing the bolt hole within 
the limits specified in the service bulletin is not adequate to 
remove the corrosion, before further flight, repair in accordance 
with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or per data meeting the type 
certification basis of the airplane approved by a Boeing Company 
Designated Engineering Representative who has been authorized by the 
Manager, Seattle ACO, to make such findings. For a repair method to 
be approved, the approval must specifically reference this AD.

Parts Installation

    (e) As of the effective date of this AD: No person may install, 
on any airplane, an H-11 steel bolt in the latch fittings of the 
main deck side cargo door, nose cargo door, or the forward and aft 
lower lobe cargo doors.

Alternative Methods of Compliance

    (f) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, 
is authorized to approve alternative methods of compliance for this 
AD.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Service Bulletin 747-53A2464, 
Revision 1, dated August 30, 2001. This incorporation by reference 
was approved by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on January 27, 2004.

    Issued in Renton, Washington, on December 11, 2003.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31195 Filed 12-22-03; 8:45 am]
BILLING CODE 4910-13-P