Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes, 14589-14592 [05-5696]

Download as PDF 14589 Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules ESTIMATED COSTS Action Work hour Average labor rate per hour Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost Inspections ............................................... 6 $65 None $390 20 $7,800 Authority for This Rulemaking The Proposed Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 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. VerDate jul<14>2003 16:19 Mar 22, 2005 Jkt 205001 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Affected ADs (b) None. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle Aircraft Certification Office (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 Delegation Option Authorization 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. Applicability (c) This AD applies to Boeing Model 747– 200C and 747–200F series airplanes, equipped with a nose cargo door, certificated in any category; as identified in paragraph 1.A.1 of Boeing Special Attention Service Bulletin 747–53–2493, dated July 3, 2003. Issued in Renton, Washington, on March 14, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–5695 Filed 3–22–05; 8:45 am] Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–20690; Directorate Identifier 2003–NM–230–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by May 9, 2005. Unsafe Condition (d) This AD was prompted by a report of a crack above the stringer (STR) 23 lap splice on a 747–200F series airplane. We are issuing this AD to detect and correct cracks or material loss in the fuselage skin, and consequent reduced structural integrity of the skin panel, which could result in rapid depressurization 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. Inspections and Repair (f) Before the accumulation of 15,000 total flight cycles, or within 1,200 flight cycles after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking, and a low frequency eddy current inspection for material loss, in the fuselage skin. Repair any crack or material loss prior to further flight. Do all actions in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2493, dated July 3, 2003. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 BILLING CODE 4910–13–P 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for E:\FR\FM\23MRP1.SGM 23MRP1 14590 Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules 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 https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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 https:// 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: VerDate jul<14>2003 16:19 Mar 22, 2005 Jkt 205001 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 https:// 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 https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://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 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 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 onetime 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. E:\FR\FM\23MRP1.SGM 23MRP1 Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules 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 14591 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 Number of airplanes Airplanes Group 1 (left and right side HFEC inspection). Group 1 (left and right side detailed inspection). Group 2 (left side HFEC inspection) ... Group 2 (left side detailed inspection) Group 3 (left and right side HFEC inspection). Group 3 (left and right side detailed inspection). Jkt 205001 Fleet cost 2 $130 ............................................ $15,470. 119 2 $130, per inspection cycle .......... $15,470, per inspection cycle. 16 16 5 1 1 2 $65 .............................................. $65, per inspection cycle ............ $130 ............................................ $4,400. $4,400, per inspection cycle. $650. 5 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: 16:19 Mar 22, 2005 Cost per airplane 119 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. VerDate jul<14>2003 Work hours 2 $130, per inspection cycle .......... $650, per inspection cycle . 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Docket No. FAA–2005–20692; Directorate Identifier 2004–NM–229–AD. BOEING: PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 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 E:\FR\FM\23MRP1.SGM 23MRP1 14592 Federal Register / Vol. 70, No. 55 / Wednesday, March 23, 2005 / Proposed Rules 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. VerDate jul<14>2003 16:19 Mar 22, 2005 Jkt 205001 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 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20688; Directorate Identifier 2004–NM–165–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 757–200 and –300 series airplanes. This proposed AD would require replacing certain electrical panels with certain new panels. This proposed AD is prompted by a report of some loose wire terminations in the P50 panel that caused intermittent indications in the flight deck. We are proposing this AD to prevent intermittent indications in the flight deck, incorrect circuitry operation in the panels, and airplane system malfunctions that may adversely affect the alternate flaps, alternate gear extension, and fire extinguishing. 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 https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 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 https:// 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– 20688; the directorate identifier for this docket is 2004–NM–165–AD. FOR FURTHER INFORMATION CONTACT: Louie Natsiopoulos, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6478; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Docket Management System (DMS) The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track each action and assign a corresponding directorate identifier. The DMS AD docket number is in the form ‘‘Docket No. FAA–2005–99999.’’ The Transport Airplane Directorate identifier is in the form ‘‘Directorate Identifier 2004–NM– 999–AD.’’ Each DMS AD docket also lists the directorate identifier (‘‘Old Docket Number’’) as a cross-reference for searching purposes. 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– 2005–20688; Directorate Identifier 2004–NM–165–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 https:// 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 E:\FR\FM\23MRP1.SGM 23MRP1

Agencies

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

-----------------------------------------------------------------------

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).

-----------------------------------------------------------------------

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 https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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
https://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 https://
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 https://dms.dot.gov.

Examining the Docket

You can examine the AD docket on the Internet at https://
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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Airplanes airplanes Work hours Cost per airplane Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
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).
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

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