Airworthiness Directives; Boeing Model 757-200, -200CB, and -200PF Series Airplanes, 16175-16177 [05-6250]

Download as PDF Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules Applicability (c) This AD applies to BAE Systems (Operations) Limited Model BAe 146 series airplanes, certificated in any category; except those on which BAe Modification HCM00972A or HCM00972C has been accomplished. left and right main landing gear (MLG) bay. We are issuing this AD to detect and correct fatigue cracking in the fuselage pressure skin above the left and right MLG bay; such fatigue cracking could adversely affect the structural integrity of the fuselage and its ability to maintain pressure differential. Unsafe Condition (d) This AD was prompted by reports of cracks in the fuselage pressure skin above the Compliance (e) You are responsible for having the actions required by this AD performed within 16175 the compliance times specified, unless the actions have already been done. Initial and Repetitive Inspections (f) At the times specified in Table 1 of this AD, inspect the fuselage pressure skin above the left and right MLG bay for cracks in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin 53–170, dated August 8, 2003. TABLE 1.—COMPLIANCE TIMES For airplanes listed in paragraph (c) of this AD— Do initial inspections— On which neither BAe modification HCM00744M nor HCM00850A has been accomplished. Prior to the accumulation of 15,000 total flight cycles or within 500 flight cycles after the effective date of this AD, whichever occurs later. At intervals not to exceed 1,000 flight cycles. On which neither BAe modification HCM00744M nor HCM00850A has been accomplished. Prior to the accumulation of 15,000 total flight cycles or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. At intervals not to exceed 3,000 flight cycles. Issued in Renton, Washington, on March 17, 2005. Jeffery E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6249 Filed 3–29–05; 8:45 am] transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are proposing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by May 16, 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 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 And do repetitive inspections thereafter— On which both BAe modification HCM00744M nor HCM00850A has been accomplished. Corrective Action (g) If any crack is found during any inspection required by paragraph (f) of this AD, do the corrective action and any related investigative actions, in accordance with the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin 53–170, dated August 8, 2003, except as required by paragraph (h) of this AD. (h) If any cracking is found during any inspection or related investigative action required by this AD, and the service bulletin recommends contacting BAe Systems for appropriate action: Before further flight, repair the cracks according to a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Civil Aviation Authority (or its delegated agent). No Reporting (i) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (k) British airworthiness directive G–2004– 0004, dated February 26, 2004, also addresses the subject of this AD. VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20726; Directorate Identifier 2004–NM–265–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757–200, –200CB, and –200PF 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, –200CB, and –200PF series airplanes. This proposed AD would require an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions and part marking if necessary. This proposed AD is prompted by a report indicating that cracked flap PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\30MRP1.SGM 30MRP1 16176 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules 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– 20726; the directorate identifier for this docket is 2004–NM–265–AD. FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6487; 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– 2005–20726; Directorate Identifier 2004–NM–265–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 a report indicating that cracked flap transmission output VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies on certain Boeing Model 757–200, –200CB, and –200 PF series airplanes. Investigation revealed that the cracks are the result of a manufacturing error in the production of transmission assemblies having certain part numbers and serial numbers. A damaged output gear could result in a disconnect within the flap transmission and cause an undetected flap skew. An undetected flap skew, if not corrected, could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability of the airplane. AD on U.S. operators is estimated to be $41,860, or $65 per airplane. Removal of a transmission assembly; removal, inspection, and reassembly of the transmission output gear; and reinstallation of the transmission assembly; if required; will take about 20 work hours per transmission assembly, at an average labor rate of $65 per work hour. Required parts will cost about $325 per transmission output gear. Based on these figures, we estimate the cost of replacement to be $1,625 per transmission output assembly (there are 8 transmission output assemblies per airplane and 325 suspect assemblies). Relevant Service Information 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. We have reviewed Boeing Special Attention Service Bulletin 757–27– 0150, dated December 9, 2004. The service bulletin describes procedures for inspecting each trailing edge flap transmission assembly to determine the part number and serial number, and related investigative and corrective actions if necessary. The related investigative and corrective actions include removing the transmission output gear from the affected transmission assembly, performing a magnetic particle inspection of the output gear, and replacing the output gear with a new output gear if any cracks or defects are found. The service bulletin also includes procedures for marking the nameplate of a trailing edge flap transmission assembly with the service bulletin number to indicate that the inspection of the output gear has been completed. 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. Costs of Compliance There are about 979 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 644 airplanes of U.S. registry. It will take approximately 1 work hour per airplane to accomplish the proposed inspection at an average labor rate of $65 per work hour. Based on this figure, the cost impact of the proposed PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Authority for This Rulemaking 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 E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules section for a location to examine the regulatory evaluation. replace that transmission output gear before further flight. List of Subjects in 14 CFR Part 39 Parts Installation (g) As of the effective date of this AD, no person may install a trailing edge flap transmission assembly, part number (P/N) 251N4050–37, –38, –39, or –40, having any serial number (S/N) 001 through 325 inclusive; or P/N 251N4022–28, –29, –30, or –31, having any S/N 001 through 325 inclusive; on any airplane; unless the transmission assembly has been inspected, and any applicable related investigative and corrective actions and part marking has been accomplished, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–27– 0150, dated December 9, 2004. 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): Boeing: Docket No. FAA–2005–20726; Directorate Identifier 2004–NM–265–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by May 16, 2005. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on March 21, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6250 Filed 3–29–05; 8:45 am] Affected ADs (b) None. BILLING CODE 4910–13–P Applicability (c) This AD applies to Boeing Model 757– 200, –200CB, and –200PF series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757–27–0150, dated December 9, 2004. DEPARTMENT OF TRANSPORTATION Unsafe Condition (d) This AD was prompted by a report indicating that cracked flap transmission output gears have been discovered during routine overhaul of the trailing edge flap transmission assemblies. We are issuing this AD to prevent an undetected flap skew, which could result in a flap loss, damage to adjacent airplane systems, and consequent reduced controllability 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. Inspection To Determine Part Number and Serial Number (f) Within 60 months after the effective date of this AD: Do an inspection of each trailing edge flap transmission assembly to determine the part number and serial number, and any applicable related investigative and corrective actions and part marking, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757–27– 0150, dated December 9, 2004. If, during any related investigative action, any transmission output gear is found with a defect or crack, VerDate jul<14>2003 14:59 Mar 29, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20725; Directorate Identifier 2003–NM–250–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 707–300B, –300C, and –400 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Boeing Model 707–300B, –300C, and –400 series airplanes. This proposed AD would require repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. This proposed AD would provide as an option a preventive modification, which would defer the repetitive inspections. This proposed AD also would provide an option of replacing all hinge fitting assemblies with new, improved parts, which would terminate the repetitive inspection requirements. This proposed AD is prompted by results of a review PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 16177 to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are proposing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard leading edge slat and could cause the flightcrew to lose control of the airplane. DATES: We must receive comments on this proposed AD by May 16, 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. You can get the service information identified in this proposed AD from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You may examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or 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. FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, Airframe Branch, ANM–120S, FAA Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98055–4056; telephone (425) 917–6428; 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–2004–99999.’’ The Transport Airplane Directorate identifier is in the form ‘‘Directorate Identifier 2004–NM– E:\FR\FM\30MRP1.SGM 30MRP1

Agencies

[Federal Register Volume 70, Number 60 (Wednesday, March 30, 2005)]
[Proposed Rules]
[Pages 16175-16177]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6250]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20726; Directorate Identifier 2004-NM-265-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200, -200CB, and -
200PF 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 certain Boeing Model 757-200, -200CB, and -200PF series airplanes. 
This proposed AD would require an inspection of each trailing edge flap 
transmission assembly to determine the part number and serial number, 
and related investigative and corrective actions and part marking if 
necessary. This proposed AD is prompted by a report indicating that 
cracked flap transmission output gears have been discovered during 
routine overhaul of the trailing edge flap transmission assemblies. We 
are proposing this AD to prevent an undetected flap skew, which could 
result in a flap loss, damage to adjacent airplane systems, and 
consequent reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 16, 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

[[Page 16176]]

of Transportation, 400 Seventh Street SW., room PL-401, on the plaza 
level of the Nassif Building, Washington, DC. This docket number is 
FAA-2005-20726; the directorate identifier for this docket is 2004-NM-
265-AD.

FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6487; 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-2005-20726; 
Directorate Identifier 2004-NM-265-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 a report indicating that cracked flap transmission 
output gears have been discovered during routine overhaul of the 
trailing edge flap transmission assemblies on certain Boeing Model 757-
200, -200CB, and -200 PF series airplanes. Investigation revealed that 
the cracks are the result of a manufacturing error in the production of 
transmission assemblies having certain part numbers and serial numbers. 
A damaged output gear could result in a disconnect within the flap 
transmission and cause an undetected flap skew. An undetected flap 
skew, if not corrected, could result in a flap loss, damage to adjacent 
airplane systems, and consequent reduced controllability of the 
airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 757-27-
0150, dated December 9, 2004. The service bulletin describes procedures 
for inspecting each trailing edge flap transmission assembly to 
determine the part number and serial number, and related investigative 
and corrective actions if necessary. The related investigative and 
corrective actions include removing the transmission output gear from 
the affected transmission assembly, performing a magnetic particle 
inspection of the output gear, and replacing the output gear with a new 
output gear if any cracks or defects are found. The service bulletin 
also includes procedures for marking the nameplate of a trailing edge 
flap transmission assembly with the service bulletin number to indicate 
that the inspection of the output gear has been completed. 
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.

Costs of Compliance

    There are about 979 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 644 airplanes of 
U.S. registry.
    It will take approximately 1 work hour per airplane to accomplish 
the proposed inspection at an average labor rate of $65 per work hour. 
Based on this figure, the cost impact of the proposed AD on U.S. 
operators is estimated to be $41,860, or $65 per airplane.
    Removal of a transmission assembly; removal, inspection, and 
reassembly of the transmission output gear; and reinstallation of the 
transmission assembly; if required; will take about 20 work hours per 
transmission assembly, at an average labor rate of $65 per work hour. 
Required parts will cost about $325 per transmission output gear. Based 
on these figures, we estimate the cost of replacement to be $1,625 per 
transmission output assembly (there are 8 transmission output 
assemblies per airplane and 325 suspect assemblies).

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

[[Page 16177]]

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-2005-20726; Directorate Identifier 2004-NM-
265-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by May 16, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 757-200, -200CB, and -200PF 
series airplanes, certificated in any category, as identified in 
Boeing Special Attention Service Bulletin 757-27-0150, dated 
December 9, 2004.

Unsafe Condition

    (d) This AD was prompted by a report indicating that cracked 
flap transmission output gears have been discovered during routine 
overhaul of the trailing edge flap transmission assemblies. We are 
issuing this AD to prevent an undetected flap skew, which could 
result in a flap loss, damage to adjacent airplane systems, and 
consequent reduced controllability 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.

Inspection To Determine Part Number and Serial Number

    (f) Within 60 months after the effective date of this AD: Do an 
inspection of each trailing edge flap transmission assembly to 
determine the part number and serial number, and any applicable 
related investigative and corrective actions and part marking, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 757-27-0150, dated December 9, 2004. If, during any related 
investigative action, any transmission output gear is found with a 
defect or crack, replace that transmission output gear before 
further flight.

Parts Installation

    (g) As of the effective date of this AD, no person may install a 
trailing edge flap transmission assembly, part number (P/N) 
251N4050-37, -38, -39, or -40, having any serial number (S/N) 001 
through 325 inclusive; or P/N 251N4022-28, -29, -30, or -31, having 
any S/N 001 through 325 inclusive; on any airplane; unless the 
transmission assembly has been inspected, and any applicable related 
investigative and corrective actions and part marking has been 
accomplished, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 757-27-0150, dated 
December 9, 2004.

Alternative Methods of Compliance (AMOCs)

    (h) The Manager, Seattle Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

    Issued in Renton, Washington, on March 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-6250 Filed 3-29-05; 8:45 am]
BILLING CODE 4910-13-P

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