[Federal Register Volume 68, Number 166 (Wednesday, August 27, 2003)]
[Proposed Rules]
[Pages 51521-51523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-21873]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-180-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing airplane models. 
This proposal would 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. This proposal also would 
require 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: Comments must be received by October 14, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-180-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-180-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Rick Kawaguchi, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6434; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-180-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-180-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report of five corroded and broken bolts 
common to two of the latch fittings for the main deck side cargo door 
on a Boeing Model 747-300 series airplane. The affected bolts are made 
from H-11 steel, a material that is susceptible to corrosion and 
subsequent stress corrosion cracking. Broken H-11 steel bolts in the 
latch fittings of the cargo door could reduce the capability of the 
door latch to keep the door closed. This condition, if not corrected, 
could result in loss of the cargo door and consequent rapid 
depressurization of the airplane.
    The same H-11 steel bolts used in the latch fittings of the main 
deck side cargo door of Boeing Model 747-300 series airplanes are also 
used in the latch fittings of the main deck side cargo door, nose cargo 
door, and the forward and aft lower lobe cargo doors on certain Boeing 
Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 
747-400, 747SR, and 747SP series airplanes. Therefore, the subject 
doors on all of these airplane models may be subject to the same unsafe 
condition.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Alert Service Bulletin 747-
53A2464, Revision 1, dated August 30, 2001. That service bulletin 
describes procedures for a one-time 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. 
The inspection procedures include

[[Page 51522]]

checking the bolt part number, which is stamped on the bolt head; or 
using a magnet to verify that the bolt is made of steel. The service 
bulletin also describes procedures for repetitive ultrasonic 
inspections for cracked or broken H-11 steel bolts, and replacement of 
H-11 steel bolts with Inconel bolts. The procedures for replacement of 
H-11 steel bolts involve 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. 
Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

Other Relevant Rulemaking

    Boeing Alert Service Bulletin 747-53A2464, Revision 1, specifies 
that the actions in Boeing Alert Service Bulletin 747-52A2167 must have 
been accomplished previously or must be accomplished concurrently. The 
FAA has previously issued AD 80-14-11, amendment 39-3831. That AD 
applies to all Model 747 series airplanes equipped with nose cargo 
doors, and requires, before further flight (as of July 15, 1980, the 
effective date of that AD), an inspection for loose or missing bolts of 
the portal latch fittings of the nose cargo door, and corrective 
actions if necessary, per Boeing Alert Service Bulletin 747-52A2167, 
Revision 1, dated March 28, 1980. Because the initial compliance time 
of AD 80-14-11 has long passed, this AD does not specify a requirement 
for accomplishing that service bulletin.

Explanation of Requirements of Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
Boeing Alert Service Bulletin 747-53A2464, Revision 1, except as 
discussed below. The actions would be required to be accomplished in 
accordance with the service bulletin described previously.

Differences Between This Proposed AD and Boeing Alert Service Bulletin 
747-53A2464, Revision 1

    The service bulletin does not specify the type of inspection 
necessary to identify H-11 steel bolts or to find corrosion during 
accomplishment of the replacement of H-11 bolts with improved bolts. 
For the purposes of this proposed AD, we have determined that the 
procedures in the service bulletin constitute a ``detailed 
inspection.'' Note 1 of this proposed AD defines such an inspection.
    Although the service bulletin specifies that the manufacturer may 
be contacted for disposition of certain repairs, this proposed AD would 
require such repairs to be accomplished per a method approved by the 
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 Aircraft Certification 
Office, to make such findings.
    The service bulletin specifies that the actions therein should be 
accomplished prior to or concurrently with the actions in Boeing 
Service Bulletin 747-52-2197. We have determined that it is not 
necessary at this time to require accomplishment of Boeing Service 
Bulletin 747-52-2197. This determination is based on our decision that 
the inspection of the portal latch fitting of the nose cargo door 
described in that service bulletin does not address an immediate safety 
issue. Service history shows that there have been no significant 
adverse findings since the issuance of that service bulletin; thus, the 
subject of that service bulletin is not an area of concern.

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in this 
proposed AD.

Change to Labor Rate Estimate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

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 
would be affected by this proposed AD, that it would take between 2 and 
8 work hours per airplane (depending on the airplane's configuration) 
to accomplish the proposed inspection, and that the average labor rate 
is $65 per work hour. Based on these figures, the cost impact of the 
proposed 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 proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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


[[Page 51523]]



PART 39--AIRWORTHINESS DIRECTIVES

    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]

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

Boeing: 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 Alert 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 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.


    Issued in Renton, Washington, on August 20, 2003.
Kyle L. Olsen,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-21873 Filed 8-26-03; 8:45 am]
BILLING CODE 4910-13-P