Airworthiness Directives; Boeing Model 777-200, -200LR, -300, and -300ER Series Airplanes, 42326-42328 [E7-15025]

Download as PDF 42326 Federal Register / Vol. 72, No. 148 / Thursday, August 2, 2007 / Proposed Rules services will be refunded to the horse’s owner or importer. * * * * * 3. Section 93.304 is amended as follows: a. In paragraph (a)(1)(ii), by removing the citation ‘‘§ 93.301(f)’’ and adding the citation ‘‘§ 93.301(f)(1)’’ in its place. b. By redesignating paragraph (a)(1)(iii) as paragraph (a)(1)(iv) and adding a new paragraph (a)(1)(iii) to read as set forth below. (3) A plan to return sick or injured horses to performance condition. (J) An application for a trust fund or escrow account agreement with APHIS in accordance with § 93.301(f)(11). * * * * * Done in Washington, DC, this 27th day of July 2007. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. E7–14994 Filed 8–1–07; 8:45 am] mstockstill on PROD1PC66 with PROPOSALS § 93.304 Import permits for horses from regions affected with CEM and for horse specimens for diagnostic purposes; reservation fees for space at quarantine facilities maintained by APHIS. BILLING CODE 3410–34–P (a) Application for permit; reservation required. (1) * * * (iii) Horses intended for importation under § 93.301(f)(2) must meet the permit requirements of paragraph (a)(1)(i) of this section. Additionally, for horses intended for importation under § 93.301(f)(2), the horse’s owner or importer must include the following information with the application for permit that is required by paragraph (a)(1)(i) of this section: (A) The individual identifying information required in paragraph (a)(1)(i) of this section for all horses to be imported. (B) The permanent electronic identification of each horse to be imported, if applicable. In the event that a horse has permanent electronic identification, the horse must be accompanied by a compatible reader. (C) Photographs (head and lateral views) that are sufficient to identify each horse on an electronic medium approved by APHIS. (D) The proposed total length of stay in the United States. (E) A description of the shows or events in which the horse will perform while in the United States. (F) The names, dates, and locations of the venues in which the horse will perform while in the United States. (G) The names and locations of the premises on which the horse will be kept while in the United States, and the dates the horse will be kept on each premises. (H) The methods and routes by which the horse will be transported while in the United States. (I) A written plan for handling sick or injured horses that includes: (1) The name, address, and phone number of each accredited veterinarian who will provide veterinary services in the United States; (2) The name, address, and phone number of medical facilities to be used to diagnose or treat sick or injured horses while in the United States; and Federal Aviation Administration VerDate Aug<31>2005 15:57 Aug 01, 2007 Jkt 211001 DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2007–28854; Directorate Identifier 2007–NM–109–AD] RIN 2120–AA64 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6443; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited Airworthiness Directives; Boeing Model 777–200, –200LR, –300, and –300ER 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 all Boeing Model 777–200, –200LR, –300, and –300ER series airplanes. This proposed AD would require doing initial and repetitive inspections for cracking of the elevator actuator fittings, and replacing any cracked fitting with a new fitting. This proposed AD results from a report that a cracked left elevator actuator fitting was found on a Model 777 airplane. We are proposing this AD to detect and correct a cracked actuator fitting, which could detach from the elevator and lead to an unrestrained elevator and an unacceptable flutter condition, which could result in loss of airplane control. DATES: We must receive comments on this proposed AD by September 17, 2007. 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: U.S. Department of Transportation, Docket Operations, M– PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28854; Directorate Identifier 2007–NM–109–AD’’ at the beginning 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 received 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 Web site, 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 may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the E:\FR\FM\02AUP1.SGM 02AUP1 Federal Register / Vol. 72, No. 148 / Thursday, August 2, 2007 / Proposed Rules ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. mstockstill on PROD1PC66 with PROPOSALS Discussion We have received a report indicating that a cracked left elevator actuator fitting was found on a Model 777 airplane with 17,346 total flight hours and 14,043 total flight cycles. The crack extended through the lower inboard flange of the fitting and into the vertical flange. Analysis by Boeing indicates that this crack resulted from fatigue due to higher than anticipated stress levels in the fitting flanges. Cracked elevator actuator fittings could lack adequate residual strength to react to design flight loads and become detached from the elevator. This condition, if not corrected, could allow a cracked actuator fitting to detach from the elevator and lead to an unrestrained elevator and an unacceptable flutter condition, which could result in loss of airplane control. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 777–55A0015, dated April 19, 2007. The service bulletin describes procedures for doing an initial dye penetrant or high-frequency eddy current (HFEC) inspection to detect cracking of the elevator actuator fittings; repetitive dye penetrant, HFEC, or detailed inspections of the fittings thereafter; and replacing any cracked fitting with a new fitting having the same part number or an approved optional part number. Compliance times for the initial inspections, depending upon airplane condition, are: • For airplanes having 14,000 total flight-cycles or more as of the date on the service bulletin, within 90 days after the date on the service bulletin; • For airplanes having 10,000 total flight-cycles or more, but less than 14,000 total flight-cycles, as of the date on the service bulletin, within 12 months after the date on the service bulletin or within 90 days after the airplane reaches 14,000 total flightcycles, whichever occurs first; or • For airplanes having less than 10,000 total flight-cycles as of the date on the service bulletin, before the accumulation of 10,000 total flight cycles or within 12 months after the date on the service bulletin, whichever occurs first. The next inspection, depending upon the type of initial inspection, is to be done at 1,000 or 1,200 flight cycles after the initial inspection, and repetitive VerDate Aug<31>2005 15:57 Aug 01, 2007 Jkt 211001 inspections thereafter are to be done at intervals not to exceed 350 to 1,200 flight cycles. Any fitting found cracked during any inspection must be replaced before further flight. Any replacement fitting must receive an initial inspection before the accumulation of 10,000 total flight cycles after the replacement date, and repetitive inspections thereafter as described in this paragraph. 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. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Interim Action We consider this proposed AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance There are about 619 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 138 airplanes of U.S. registry. The proposed inspections would take about 4 work hours per airplane, per inspection cycle, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $44,160, or $320 per airplane, per inspection cycle. 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 42327 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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28854; Directorate Identifier 2007–NM–109–AD. Comments Due Date (a) The FAA must receive comments on this AD action by September 17, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category. E:\FR\FM\02AUP1.SGM 02AUP1 42328 Federal Register / Vol. 72, No. 148 / Thursday, August 2, 2007 / Proposed Rules Unsafe Condition (d) This AD results from a report that a cracked left elevator actuator fitting was found on a Model 777 airplane. We are issuing this AD to detect and correct a cracked actuator fitting, which could detach from the elevator and lead to an unrestrained elevator and an unacceptable flutter condition, which could result in loss of airplane control. Issued in Renton, Washington, on July 25, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–15025 Filed 8–1–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 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. Federal Aviation Administration 14 CFR Part 39 Inspections (f) At the applicable time specified in paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 777–55A0015, dated April 19, 2007, do an initial dye penetrant or highfrequency eddy current (HFEC) inspection for cracking of the elevator actuator fittings, and, thereafter, do repetitive dye penetrant, HFEC, or detailed inspections at the applicable times specified in paragraph 1.E. ‘‘Compliance.’’ Before further flight, replace any fitting found to be cracked during any inspection required by this AD with a new fitting having the same part number, or an optional part number as identified in the service bulletin. Thereafter, do initial and repetitive inspections of the replacement fitting as described in paragraph 1.E. of the service bulletin. Do all inspections and actions described in this paragraph in accordance with the Accomplishment Instructions of the alert service bulletin; except, where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. mstockstill on PROD1PC66 with PROPOSALS 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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) 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 Commercial Airplanes 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. VerDate Aug<31>2005 15:57 Aug 01, 2007 Jkt 211001 [Docket No. FAA–2007–28855; Directorate Identifier 2007–NM–098–AD] RIN 2120–AA64 Airworthiness Directives; EMBRAER Model EMB–120, –120ER, –120FC, –120QC, and –120RT Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Icing tunnel tests on an EMB–120 wing section, conducted under a joint Embraer– NASA–(National Aeronautics and Space ´ Administration) FAA–CTA (Centro Tecnico Aeroespacial) research program well after the EMB–120( ) was type-certificated, have shown that stick shaker to stick pusher speed margins may drop below the minimum required by the applicable regulations in certain icing conditions. Although flight tests have shown that the aircraft handling qualities are not adversely affected, these reduced speed margins may significantly increase crew workload in certain flight phases. The unsafe condition is reduced ability of the flightcrew to maintain the safe flight and landing of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by September 4, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions for submitting comments. Examining the AD Docket You may examine the AD docket on the Internet at https://dms.dot.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28855; Directorate Identifier 2007–NM–098–AD’’ at the beginning of E:\FR\FM\02AUP1.SGM 02AUP1

Agencies

[Federal Register Volume 72, Number 148 (Thursday, August 2, 2007)]
[Proposed Rules]
[Pages 42326-42328]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-15025]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28854; Directorate Identifier 2007-NM-109-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200, -200LR, -300, and 
-300ER 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 all Boeing Model 777-200, -200LR, -300, and -300ER series 
airplanes. This proposed AD would require doing initial and repetitive 
inspections for cracking of the elevator actuator fittings, and 
replacing any cracked fitting with a new fitting. This proposed AD 
results from a report that a cracked left elevator actuator fitting was 
found on a Model 777 airplane. We are proposing this AD to detect and 
correct a cracked actuator fitting, which could detach from the 
elevator and lead to an unrestrained elevator and an unacceptable 
flutter condition, which could result in loss of airplane control.

DATES: We must receive comments on this proposed AD by September 17, 
2007.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6443; 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 in the ADDRESSES section. Include the docket number ``FAA-2007-
28854; Directorate Identifier 2007-NM-109-AD'' at the beginning 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 received 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 Web site, 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 may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the

[[Page 42327]]

ground floor of the West Building at the DOT street address stated in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after the Docket Management System receives them.

Discussion

    We have received a report indicating that a cracked left elevator 
actuator fitting was found on a Model 777 airplane with 17,346 total 
flight hours and 14,043 total flight cycles. The crack extended through 
the lower inboard flange of the fitting and into the vertical flange. 
Analysis by Boeing indicates that this crack resulted from fatigue due 
to higher than anticipated stress levels in the fitting flanges. 
Cracked elevator actuator fittings could lack adequate residual 
strength to react to design flight loads and become detached from the 
elevator. This condition, if not corrected, could allow a cracked 
actuator fitting to detach from the elevator and lead to an 
unrestrained elevator and an unacceptable flutter condition, which 
could result in loss of airplane control.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 777-55A0015, dated 
April 19, 2007. The service bulletin describes procedures for doing an 
initial dye penetrant or high-frequency eddy current (HFEC) inspection 
to detect cracking of the elevator actuator fittings; repetitive dye 
penetrant, HFEC, or detailed inspections of the fittings thereafter; 
and replacing any cracked fitting with a new fitting having the same 
part number or an approved optional part number. Compliance times for 
the initial inspections, depending upon airplane condition, are:
     For airplanes having 14,000 total flight-cycles or more as 
of the date on the service bulletin, within 90 days after the date on 
the service bulletin;
     For airplanes having 10,000 total flight-cycles or more, 
but less than 14,000 total flight-cycles, as of the date on the service 
bulletin, within 12 months after the date on the service bulletin or 
within 90 days after the airplane reaches 14,000 total flight-cycles, 
whichever occurs first; or
     For airplanes having less than 10,000 total flight-cycles 
as of the date on the service bulletin, before the accumulation of 
10,000 total flight cycles or within 12 months after the date on the 
service bulletin, whichever occurs first.

The next inspection, depending upon the type of initial inspection, is 
to be done at 1,000 or 1,200 flight cycles after the initial 
inspection, and repetitive inspections thereafter are to be done at 
intervals not to exceed 350 to 1,200 flight cycles. Any fitting found 
cracked during any inspection must be replaced before further flight. 
Any replacement fitting must receive an initial inspection before the 
accumulation of 10,000 total flight cycles after the replacement date, 
and repetitive inspections thereafter as described in this paragraph.

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. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously.

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we might consider additional rulemaking.

Costs of Compliance

    There are about 619 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 138 airplanes of 
U.S. registry. The proposed inspections would take about 4 work hours 
per airplane, per inspection cycle, at an average labor rate of $80 per 
work hour. Based on these figures, the estimated cost of the proposed 
AD for U.S. operators is $44,160, or $320 per airplane, per inspection 
cycle.

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-28854; Directorate Identifier 2007-NM-
109-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
17, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 777-200, -200LR, -300, 
and -300ER series airplanes, certificated in any category.

[[Page 42328]]

Unsafe Condition

    (d) This AD results from a report that a cracked left elevator 
actuator fitting was found on a Model 777 airplane. We are issuing 
this AD to detect and correct a cracked actuator fitting, which 
could detach from the elevator and lead to an unrestrained elevator 
and an unacceptable flutter condition, which could result in loss of 
airplane control.

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

    (f) At the applicable time specified in paragraph 1.E. 
``Compliance'' of Boeing Alert Service Bulletin 777-55A0015, dated 
April 19, 2007, do an initial dye penetrant or high-frequency eddy 
current (HFEC) inspection for cracking of the elevator actuator 
fittings, and, thereafter, do repetitive dye penetrant, HFEC, or 
detailed inspections at the applicable times specified in paragraph 
1.E. ``Compliance.'' Before further flight, replace any fitting 
found to be cracked during any inspection required by this AD with a 
new fitting having the same part number, or an optional part number 
as identified in the service bulletin. Thereafter, do initial and 
repetitive inspections of the replacement fitting as described in 
paragraph 1.E. of the service bulletin. Do all inspections and 
actions described in this paragraph in accordance with the 
Accomplishment Instructions of the alert service bulletin; except, 
where the service bulletin specifies a compliance time after the 
date on the service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) 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 Commercial Airplanes 
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.

    Issued in Renton, Washington, on July 25, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-15025 Filed 8-1-07; 8:45 am]
BILLING CODE 4910-13-P