[Federal Register Volume 70, Number 55 (Wednesday, March 23, 2005)]
[Proposed Rules]
[Pages 14589-14592]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5696]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20692; Directorate Identifier 2004-NM-229-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for

[[Page 14590]]

certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. This 
proposed AD would require doing a one-time high-frequency eddy current 
inspection and repetitive detailed inspections for cracks in the frame 
web of main entry door number 1; and repairing the door frame web if 
necessary. This proposed AD would also provide for optional terminating 
action for the repetitive inspections. This proposed AD is prompted by 
reports of cracking at the upper aft corner of the cutout for main 
entry door number 1 in the station 488 frame web. We are proposing this 
AD to detect and correct cracks in the frame web. These cracks could 
cause the frame to break and lead to rapid decompression of the 
airplane.

DATES: We must receive comments on this proposed AD by May 9, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-20692; the directorate identifier for this docket is 
2004-NM-229-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20692; 
Directorate Identifier 2004-NM-229-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that website, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    We have received reports indicating that operators have found 
several cracks in the station 488 frame web at the upper aft corner of 
the cutout for main entry door number 1 on at least three Boeing Model 
747-200B series airplanes. Cracks were found in the web common to the 
door stop number 9 fastener holes on one of the airplanes, and at the 
tooling hole in the web above stringer 17 on two other airplanes. The 
manufacturer found similar cracks on a Model 747-100SR fatigue test 
airplane and determined the cracks were caused by fatigue due to cabin 
pressurization cyclic loading. This condition, if not detected and 
corrected in a timely manner, could cause the frame to break and lead 
to rapid decompression of the airplane.

Similar Models

    The main entry door frame webs on certain Model 747-100, 747-100B, 
747-100B SUD, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes are similar to those on the affected Model 747-200B series 
airplanes. Therefore, all of these models may be subject to the same 
unsafe condition.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2508, dated 
August 19, 2004. The service bulletin describes procedures for doing a 
one-time high-frequency eddy current (HFEC) inspection for cracks in 
the forward side of the station 488 door frame web at the tooling hole 
above stringer 17 and around door stop number 9; for doing repetitive 
detailed inspections for cracks in the forward side of the station 488 
door frame web between door stop number 8 and the upper door sill; and 
for repairing the door frame web if necessary. Repairing the door frame 
web would eliminate the need for repetitive detailed inspections.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Referenced Service Bulletin.''

Difference Between the Proposed AD and Referenced Service Bulletin

    The service bulletin specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair those conditions in one of 
the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Delegation Option Authorization Organization whom we 
have authorized to make those findings.

[[Page 14591]]

Clarification of References to Additional Service Information

    Boeing Alert Service Bulletin 747-53A2508 also identifies Boeing 
Service Bulletin 747-53-2349 (cited in AD 2002-10-10, amendment 39-
12756 (67 FR 36081, dated May 23, 2002)), and Boeing Alert Service 
Bulletin 747-53A2265 (cited in AD 91-11-01, amendment 39-6997 (56 FR 
22306, dated May 15, 1991)), as alternative sources of information for 
accomplishing the repetitive detailed inspections specified in this 
proposed AD.
    Boeing Alert Service Bulletin 747-53A2508 refers to Boeing Service 
Bulletin 747-53-2272 as an alternative for accomplishing the open-hole 
HFEC inspection of the frame inner chord specified in this proposed AD. 
If the frame inner chord replacement required by AD 91-11-01 (which 
refers to Service Bulletin 747-53-2272 as a source of service 
information) is being done concurrently with the repair of the door 
frame web at station 488 specified in this proposed AD, the open-hole 
HFEC inspection specified in this proposed AD is unnecessary.

Costs of Compliance

    There are about 274 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 140 airplanes of 
U.S. registry. The following table, using an estimated labor rate of 
$65 per work hour, provides the estimated costs for U.S. operators to 
comply with this proposed AD.

                                                                    Inspection Costs
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                                    Number of
           Airplanes                airplanes      Work hours                 Cost per airplane                               Fleet cost
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Group 1 (left and right side                119               2  $130.......................................  $15,470.
 HFEC inspection).
Group 1 (left and right side                119               2  $130, per inspection cycle.................  $15,470, per inspection cycle.
 detailed inspection).
Group 2 (left side HFEC                      16               1  $65........................................  $4,400.
 inspection).
Group 2 (left side detailed                  16               1  $65, per inspection cycle..................  $4,400, per inspection cycle.
 inspection).
Group 3 (left and right side                  5               2  $130.......................................  $650.
 HFEC inspection).
Group 3 (left and right side                  5               2  $130, per inspection cycle.................  $650, per inspection cycle .
 detailed inspection).
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Boeing: Docket No. FAA-2005-20692; Directorate Identifier 2004-NM-
229-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by May 9, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series 
airplanes, certificated in any category; as identified in Boeing 
Alert Service Bulletin 747-53A2508, dated August 19, 2004.

Unsafe Condition

    (d) This AD was prompted by reports of cracking at the upper aft 
corner of the cutout for main entry door number 1 in the station 488 
frame web. We are issuing this AD to detect and correct cracks in 
the frame web. These cracks could cause the frame to break and lead 
to rapid decompression of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Initial Inspections

    (f) Before the accumulation of 16,000 total flight cycles, or 
within 1,000 flight cycles after the effective date of this AD, 
whichever occurs later, do a high frequency eddy current (HFEC) 
inspection and a detailed inspection of the station 488 frame web, 
by doing all of the actions specified in the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2508, dated 
August

[[Page 14592]]

19, 2004; except as provided by paragraph (h) or (j) of this AD.

Repetitive Inspections

    (g) If no crack is found during the inspections required by 
paragraph (f) of this AD, repeat the detailed inspection required by 
paragraph (f) of this AD at the applicable time specified in 
paragraph (g)(1) or (g)(2) of this AD.
    (1) For airplanes identified in the service bulletin as Groups 1 
and 2: At intervals not to exceed 3,000 flight cycles.
    (2) For airplanes identified in the service bulletin as Group 3: 
At intervals not to exceed 1,500 flight cycles.

Repairs

    (h) If any crack in the main entry door frame web is found 
during any inspection required by this AD: Before further flight, 
repair in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2508, dated August 19, 2004. Where the 
service bulletin specifies to contact Boeing for appropriate action: 
Before further flight, repair the door frame web and any frame chord 
damage according to a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or according to data 
meeting the type certification basis of the airplane approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization (DOA) Organization who has been authorized by the 
Manager, Seattle ACO, to make those findings. For a repair method to 
be approved, the approval must specifically reference this AD.

Termination of Repeat Inspections

    (i) For the repaired frame web only, accomplishing the door 
frame web repair required by paragraph (h) of this AD ends the 
repetitive inspections required by paragraph (g) of this AD.

Credit for Accomplishing HFEC Inspection Using Alternate Service 
Information

    (j) If the frame inner chord replacement required by AD 91-11-01 
(which identifies Service Bulletin 747-53-2272 as a source of 
service information) is accomplished concurrently with the repair of 
the station 488 door frame web specified by paragraph (h) of this 
AD, the HFEC inspection required paragraph (f) of this AD is not 
required.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing DOA Organization who has 
been authorized by the Manager, Seattle ACO, to make those findings. 
For a repair method to be approved, the repair must meet the 
certification basis of the airplane, and the approval must 
specifically refer to this AD.

    Issued in Renton, Washington, on March 14, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5696 Filed 3-22-05; 8:45 am]
BILLING CODE 4910-13-P