Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters, 7063-7065 [05-2608]

Download as PDF Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules to operate the helicopter to a location where the requirements of this AD can be accomplished, provided that no fracture or crack or looseness was found during the inspections required by this AD. Note: The subject of this AD is addressed in Ente Nazionale per l’Aviazione Civile (Italy) AD No. 2004–099, dated March 29, 2004. 14 CFR Part 39 Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 2004–SW– 16–AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. You may also send comments electronically to the Rules Docket at the following address: 9-asw-adcomments@faa.gov. Comments may be inspected at the Office of the Regional Counsel between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aviation Safety Engineers, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627–5232, fax (562) 627–5210. SUPPLEMENTARY INFORMATION: [Docket No. 2004–SW–16–AD] Comments Invited RIN 2120–AA64 Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments will be considered before taking action on the proposed rule. The proposals contained in this document may be changed in light of the comments received. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their mailed comments submitted in response to this proposal must submit a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket No. 2004–SW– 16–AD.’’ The postcard will be date stamped and returned to the commenter. Issued in Fort Worth, Texas, on February 1, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2591 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Airworthiness Directives; MD Helicopters, Inc. Model 600N Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes superseding an existing airworthiness directive (AD) for the MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD currently requires certain inspections of both upper tailboom attachments, nutplates, and angles for a crack or thread damage, and repairing or replacing any cracked or damaged part. Also, that AD requires replacing certain tailboom attachment bolts, adding a washer to each bolt, and modifying both upper access covers. This action would require installing six additional inspection holes in the aft fuselage skin panels and inspecting the upper and lower tailboom attachment fittings, the upper longerons, and the angles and nutplates for cracks. Also, the AD would provide a terminating action of modifying the fuselage aft section to strengthen the tailboom attachments and longerons. This proposal is prompted by an analysis that shows that certain tailboom attachments and longerons may develop cracks. The actions specified by the proposed AD are intended to prevent failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before April 11, 2005. VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 ADDRESSES: Discussion On November 28, 2001, the FAA issued Emergency AD 2001–24–51 for MDHI Model 600N helicopters and issued the final rule; request for comments on April 2, 2002 (Amendment 39–12706 (67 FR 17934, PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 7063 April 12, 2002)). That AD requires implementing the procedures described in MD Helicopters, Inc. Service Bulletin SB600N–03, dated November 2, 2001 (SB600N–03), for inspecting both upper tailboom attachments, nutplates, and angles for a crack or thread damage and repairing or replacing damaged parts. In addition, if one bolt is broken, the AD requires replacing all four bolts. Also, adding a washer to each bolt and modifying both upper access covers as well as a 25-hour time-in-service (TIS) repetitive borescope inspection of the tailboom attachments, nutplates, and angles is required. That action was prompted by the discovery of cracked bolts and attachments on several helicopters. The requirements of that AD are intended to prevent failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter. Since issuing that AD, the FAA has reviewed an analysis by the manufacturer and has determined that the tailboom fittings, part number (P/N) 500N3422–BSC (BSC is interchangeable with basic) and –3, and the upper longerons, P/N 500N3120–3 and –4, will develop cracks due to the same design error as the current AD. Also, the FAA has reviewed MDHI Service Bulletin SB600N–039, dated December 9, 2003, which provides information pertaining to adding six inspection holes in the fuselage and certain inspections of the tailboom attachment fittings and upper longerons for cracks. Also, MDHI has issued Technical Bulletin TB 600N–007, dated January 12, 2004, which provides information pertaining to modifying the fuselage aft section to strengthen tailboom attachment fittings and longerons. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, the proposed AD would supersede AD 2001–24–51 to require the following: • Before further flight, drill an inspection hole at fuselage station L167 and R167 (L indicates Left and R indicates Right) on each side of the fuselage. • Within 25 hours time-in-service (TIS): • Drill two additional inspection holes on each side of the fuselage at L166, R166, L153, and R153. • Visually inspect the lower attachment fittings and the upper longerons through inspection holes at L166, R166, L153 and R153, respectively. • Thereafter, at specified intervals, remove the plug buttons from the inspection holes at L167, R167, L166, E:\FR\FM\10FEP1.SGM 10FEP1 7064 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules and R166. Using a bright light, inspect the attachment fittings, angles, and nutplates for a crack. Through inspection holes L153 and R153, using a bright light and mirror or borescope, visually inspect the bottom surface of each longeron for a crack. • Before further flight, replace any cracked attachment fitting, angle, nutplate, longeron, and any nutplate with thread damage with an appropriate airworthy part. This action proposes to require that operators modify the aft fuselage to strengthen the tailboom attachments and longeron within 4 years, which would constitute terminating action for the requirements of the AD. The FAA estimates that this proposed AD would affect 39 helicopters of U.S. registry. The proposed actions would take about 322 work hours to modify and inspect the fuselage aft section per helicopter at an average labor rate of $65 per work hour. Required parts would cost approximately $14,960 per helicopter. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $1,399,710. Regulatory Findings The regulations proposed herein would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this proposal would not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this proposed regulation (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft economic evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. 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 VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: 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. Section 39.13 is amended by removing Amendment 39–12706 (67 FR 17934) and by adding a new airworthiness directive (AD), to read as follows: MD Helicopters, Inc.: Docket No. 2004–SW– 16–AD. Supersedes AD 2001–24–51, Amendment 39–12706, Docket No. 2001–SW–57–AD. Applicability: Model 600N, serial numbers with a prefix of ‘‘RN’’ 003 through 066 and 068, that have not been modified by following the Accomplishment Instructions of MDHI Technical Bulletin TB600N–007, dated January 12, 2004, certificated in any category. Compliance: Required as indicated. To prevent failure of a tailboom attachment, loss of the tailboom, and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight, unless accomplished previously, drill an inspection hole at fuselage station L167 and R167 (L indicates Left and R indicates Right) on each side of the fuselage by following the Accomplishment Instructions, paragraph 2.B.(6) of MD Helicopters, Inc. (MDHI) Service Bulletin SB600N–036, dated November 2, 2001. (b) Within 25 hours time-in-service (TIS), unless accomplished previously: (1) Drill two additional inspection holes (L166 and L153 on the left side and R166 and PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 R153 on the right side) on each side of the fuselage as shown for the left side of the fuselage in Figure 1 of MDHI SB600N–039, dated December 9, 2003 (SB–039), by following the Accomplishment Instruction paragraphs of SB–039 as follows: (i) Paragraphs 2.A.(1)(a), (b), and (d) for inspection holes at L166 and R166; (ii) Paragraphs 2.A.(2)(a), (b), and (d) for inspection holes at L153 and R153; and (2) Visually inspect for a crack by following the Accomplishment Instruction paragraphs of SB–039 at the following locations, except you are not required to contact MDHI. (i) The lower left and right attachment fittings through inspection holes at L166 and R166, paragraph 2.A.(1)(c). (ii) The upper left and right longerons through inspection holes at L153 and R153, paragraph 2.A.(2)(c). Note: The reference in Figure 1 of SB–039 to inspection hole at L167 mistakenly states that it was ‘‘Added by SB900–036.’’ Inspection holes at L167 and R167 were originally specified by SB600N–036. (c) Thereafter, at the specified intervals, remove the plug buttons from the inspection holes, and using a bright light, inspect the upper left and upper right attachment fittings, angles, and nutplates for a crack by following the Accomplishment Instruction paragraphs of SB–039, as follows, except you are not required to contact MDHI. (1) At intervals not to exceed 25 hours TIS, for inspection holes at L167 and R167, inspect the upper left and upper right attachment fittings, angles, and nutplates by following paragraphs 2.B.(2) through 2.B.(4). (2) At intervals not to exceed 100 hours TIS, for inspection holes at L166 and R166, inspect the lower left and lower right attachment fittings, angles, and nutplates by following paragraphs 2.B.(2) through 2.B.(4). (3) At intervals not to exceed 1200 hours TIS, for inspection holes L153 and R153 using a mirror or borescope, inspect the bottom surface of each longeron by following paragraphs 2.C.(2) and 2.C.(3). (d) Before further flight, replace any cracked attachment fitting, angle, nutplate, longeron, and any nutplate with thread damage with an appropriate airworthy part. (e) On or before 4 years from the effective date of this AD, modify the aft fuselage to strengthen the tailboom attachments and the longerons by following the Accomplishment Instructions of MDHI Technical Bulletin TB600N–007, dated January 12, 2004 (TB– 007). Modifying the aft fuselage by following TB–007 constitutes terminating action for the requirements of this AD. (f) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Los Angeles Aircraft Certification Office (LAACO), FAA, for information about previously approved alternative methods of compliance. E:\FR\FM\10FEP1.SGM 10FEP1 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules Issued in Fort Worth, Texas, on February 2, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05–2608 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [COTP San Juan 05–007] RIN 1625–AA87 Security Zone: HOVENSA Refinery, St. Croix, United States Virgin Islands Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: ACTION: SUMMARY: The Coast Guard proposes to establish a permanent security zone in the vicinity of the HOVENSA refinery facility on St. Croix, U. S. Virgin Islands. The security zone is needed for national security reasons to protect the public and the HOVENSA facility from potential subversive acts. The proposed rule would exclude entry into the proposed permanent security zone by all vessels without permission of the U.S. Coast Guard Captain of the Port San Juan or a scheduled arrival in accordance with the Notice of Arrival requirements of 33 CFR part 160, subpart C. DATES: Comments and related material must reach the Coast Guard on or before March 28, 2005. ADDRESSES: You may mail comments and related material to Sector San Juan, 5 Calle La Puntilla, San Juan, PR 00901. Sector San Juan Waterways Management will maintain the public docket for this rulemaking. Comments and material received from the public, as well as documents indicated in this preamble as being available in the docket, will become part of this docket and will be available for inspection or copying at Resident Inspections Office in St. Croix, United States Virgin Island between 7 a.m. and 3:30 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Lieutenant Junior Grade Katiuska Pabon of Sector San Juan Waterways Management at 787–289–0739. SUPPLEMENTARY INFORMATION: Request for Comments We encourage you to participate in this rulemaking by submitting VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 comments and related material. If you do so, please include your name and address, identify the docket number for this rulemaking (COTP San Juan–05– 007), indicate the specific section of this document to which each comment applies, and give the reason for each comment. Please submit all comments and related material in an unbound format, no larger than 81⁄2 by 11 inches, suitable for copying. If you would like to know that your submission reached us, please enclose a stamped, selfaddressed postcard or envelope. We will consider all comments and material received during the comment period. We may change this proposed rule in view of them. Public Meeting We do not now plan to hold a public meeting. But you may submit a request for a meeting by writing to SECTOR San Juan at the address under ADDRESSES explaining why one would be beneficial. If we determine that one would aid this rulemaking, we will hold one at a time and place announced by a later notice in the Federal Register. Background and Purpose The Coast Guard has published similar temporary security zones in the Federal Register at 67 FR 2332, January 17, 2002; 67 FR 57952, September 13, 2002; 68 FR 22296, April 28, 2003; 68 FR 41081, July 10, 2003; 69 FR 6150, February 10, 2004; 69 FR 29232, May 21, 2004; and 70 FR 2950, January 19, 2005. Given the highly volatile nature of the substances stored at the HOVENSA facility, the Coast Guard recognizes that it could be a potential terrorist target and there is a continuing risk that subversive activity could be launched by vessels or persons in close proximity to the facility. This activity could be directed against tank vessels and the waterfront facility. This security zone is necessary to decrease the risk that subversive activity could be launched against the HOVENSA facility. The Captain of the Port San Juan is reducing risk by prohibiting all vessels without a scheduled arrival in accordance with the Notice of Arrival requirements of 33 CFR part 160, subpart C from entering within approximately 2 miles of the HOVENSA facility unless specifically authorized by the Captain of the Port San Juan. Discussion of Proposed Rule The proposed permanent security zone around the HOVENSA facility would be encompassed by a line connecting the following coordinates: 17°41′31″ North, 64°45′09″ West; 17°39′36″ North, 64°44′12″ West; PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 7065 17°40′00″ North, 64°43′36″ West; and 17°41′48″ North, 64°44′25″ West, and back to the point of origin. The security zone includes the waters extending approximately 2 miles seaward from the HOVENSA facility, Limetree Bay Channel and Limetree Bay. All coordinates are based upon North American Datum 1983 (NAD 1983). All vessels without a scheduled arrival in accordance with the Notice of Arrival requirements of 33 CFR part 160, subpart C are excluded from the zone unless specifically authorized by the Captain of the Port San Juan. Regulatory Evaluation This proposed rule is not a ‘‘significant regulatory action’’ under section 3(f) of Executive Order 12866, Regulatory Planning and Review, and does not require an assessment of potential costs and benefits under section 6(a)(3) of that Order. The Office of Management and Budget has not reviewed it under that Order. It is not ‘‘significant’’ under the regulatory policies and procedures of the Department of Homeland Security (DHS). We expect the economic impact of this proposed rule to be so minimal that a full Regulatory Evaluation under the regulatory policies and procedures of DHS is unnecessary. The burden imposed on the public by this rule is minimal and mariners may obtain permission to enter the zone from the Coast Guard Captain of the Port San Juan or by scheduling vessel arrival in accordance with the Notice of Arrival requirements of 33 CFR part 160, subpart C. Small Entities Under the Regulatory Flexibility Act (5 U.S.C. 601–612), we have considered whether this proposed rule would have a significant economic impact on a substantial number of small entities. The term ‘‘small entities’’ comprises small businesses, not-for-profit organizations that are independently owned and operated and are not dominant in their fields, and governmental jurisdictions with populations of less than 50,000. The Coast Guard certifies under 5 U.S.C. 605(b) that this proposed rule would not have a significant economic impact on a substantial number of small entities. The factual basis for this certification is as follows: (1) Owners of small charter fishing or diving operations that operate near the HOVENSA facility may be affected by the existence of this security zone. E:\FR\FM\10FEP1.SGM 10FEP1

Agencies

[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7063-7065]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2608]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-SW-16-AD]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters, Inc. Model 600N 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for the MD Helicopters, Inc. (MDHI) Model 600N 
helicopters. That AD currently requires certain inspections of both 
upper tailboom attachments, nutplates, and angles for a crack or thread 
damage, and repairing or replacing any cracked or damaged part. Also, 
that AD requires replacing certain tailboom attachment bolts, adding a 
washer to each bolt, and modifying both upper access covers. This 
action would require installing six additional inspection holes in the 
aft fuselage skin panels and inspecting the upper and lower tailboom 
attachment fittings, the upper longerons, and the angles and nutplates 
for cracks. Also, the AD would provide a terminating action of 
modifying the fuselage aft section to strengthen the tailboom 
attachments and longerons. This proposal is prompted by an analysis 
that shows that certain tailboom attachments and longerons may develop 
cracks. The actions specified by the proposed AD are intended to 
prevent failure of a tailboom attachment, loss of the tailboom, and 
subsequent loss of control of the helicopter.

DATES: Comments must be received on or before April 11, 2005.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2004-SW-16-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: 9-asw-adcomments@faa.gov. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aviation Safety 
Engineers, FAA, Los Angeles Aircraft Certification Office, Airframe 
Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone 
(562) 627-5232, fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2004-SW-16-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    On November 28, 2001, the FAA issued Emergency AD 2001-24-51 for 
MDHI Model 600N helicopters and issued the final rule; request for 
comments on April 2, 2002 (Amendment 39-12706 (67 FR 17934, April 12, 
2002)). That AD requires implementing the procedures described in MD 
Helicopters, Inc. Service Bulletin SB600N-03, dated November 2, 2001 
(SB600N-03), for inspecting both upper tailboom attachments, nutplates, 
and angles for a crack or thread damage and repairing or replacing 
damaged parts. In addition, if one bolt is broken, the AD requires 
replacing all four bolts. Also, adding a washer to each bolt and 
modifying both upper access covers as well as a 25-hour time-in-service 
(TIS) repetitive borescope inspection of the tailboom attachments, 
nutplates, and angles is required. That action was prompted by the 
discovery of cracked bolts and attachments on several helicopters. The 
requirements of that AD are intended to prevent failure of a tailboom 
attachment, loss of the tailboom, and subsequent loss of control of the 
helicopter.
    Since issuing that AD, the FAA has reviewed an analysis by the 
manufacturer and has determined that the tailboom fittings, part number 
(P/N) 500N3422-BSC (BSC is interchangeable with basic) and -3, and the 
upper longerons, P/N 500N3120-3 and -4, will develop cracks due to the 
same design error as the current AD. Also, the FAA has reviewed MDHI 
Service Bulletin SB600N-039, dated December 9, 2003, which provides 
information pertaining to adding six inspection holes in the fuselage 
and certain inspections of the tailboom attachment fittings and upper 
longerons for cracks. Also, MDHI has issued Technical Bulletin TB 600N-
007, dated January 12, 2004, which provides information pertaining to 
modifying the fuselage aft section to strengthen tailboom attachment 
fittings and longerons.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design. Therefore, the 
proposed AD would supersede AD 2001-24-51 to require the following:
     Before further flight, drill an inspection hole at 
fuselage station L167 and R167 (L indicates Left and R indicates Right) 
on each side of the fuselage.
     Within 25 hours time-in-service (TIS):
     Drill two additional inspection holes on each side of the 
fuselage at L166, R166, L153, and R153.
     Visually inspect the lower attachment fittings and the 
upper longerons through inspection holes at L166, R166, L153 and R153, 
respectively.
     Thereafter, at specified intervals, remove the plug 
buttons from the inspection holes at L167, R167, L166,

[[Page 7064]]

and R166. Using a bright light, inspect the attachment fittings, 
angles, and nutplates for a crack. Through inspection holes L153 and 
R153, using a bright light and mirror or borescope, visually inspect 
the bottom surface of each longeron for a crack.
     Before further flight, replace any cracked attachment 
fitting, angle, nutplate, longeron, and any nutplate with thread damage 
with an appropriate airworthy part.
    This action proposes to require that operators modify the aft 
fuselage to strengthen the tailboom attachments and longeron within 4 
years, which would constitute terminating action for the requirements 
of the AD.
    The FAA estimates that this proposed AD would affect 39 helicopters 
of U.S. registry. The proposed actions would take about 322 work hours 
to modify and inspect the fuselage aft section per helicopter at an 
average labor rate of $65 per work hour. Required parts would cost 
approximately $14,960 per helicopter. Based on these figures, we 
estimate the total cost impact of the proposed AD on U.S. operators to 
be $1,399,710.

Regulatory Findings

    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
economic evaluation prepared for this action is contained in the Rules 
Docket. A copy of it may be obtained by contacting the Rules Docket at 
the location provided under the caption ADDRESSES.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-12706 (67 FR 
17934) and by adding a new airworthiness directive (AD), to read as 
follows:

MD Helicopters, Inc.: Docket No. 2004-SW-16-AD. Supersedes AD 2001-
24-51, Amendment 39-12706, Docket No. 2001-SW-57-AD.

    Applicability: Model 600N, serial numbers with a prefix of 
``RN'' 003 through 066 and 068, that have not been modified by 
following the Accomplishment Instructions of MDHI Technical Bulletin 
TB600N-007, dated January 12, 2004, certificated in any category.
    Compliance: Required as indicated.
    To prevent failure of a tailboom attachment, loss of the 
tailboom, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Before further flight, unless accomplished previously, drill 
an inspection hole at fuselage station L167 and R167 (L indicates 
Left and R indicates Right) on each side of the fuselage by 
following the Accomplishment Instructions, paragraph 2.B.(6) of MD 
Helicopters, Inc. (MDHI) Service Bulletin SB600N-036, dated November 
2, 2001.
    (b) Within 25 hours time-in-service (TIS), unless accomplished 
previously:
    (1) Drill two additional inspection holes (L166 and L153 on the 
left side and R166 and R153 on the right side) on each side of the 
fuselage as shown for the left side of the fuselage in Figure 1 of 
MDHI SB600N-039, dated December 9, 2003 (SB-039), by following the 
Accomplishment Instruction paragraphs of SB-039 as follows:
    (i) Paragraphs 2.A.(1)(a), (b), and (d) for inspection holes at 
L166 and R166;
    (ii) Paragraphs 2.A.(2)(a), (b), and (d) for inspection holes at 
L153 and R153; and
    (2) Visually inspect for a crack by following the Accomplishment 
Instruction paragraphs of SB-039 at the following locations, except 
you are not required to contact MDHI.
    (i) The lower left and right attachment fittings through 
inspection holes at L166 and R166, paragraph 2.A.(1)(c).
    (ii) The upper left and right longerons through inspection holes 
at L153 and R153, paragraph 2.A.(2)(c).

    Note: The reference in Figure 1 of SB-039 to inspection hole at 
L167 mistakenly states that it was ``Added by SB900-036.'' 
Inspection holes at L167 and R167 were originally specified by 
SB600N-036.

    (c) Thereafter, at the specified intervals, remove the plug 
buttons from the inspection holes, and using a bright light, inspect 
the upper left and upper right attachment fittings, angles, and 
nutplates for a crack by following the Accomplishment Instruction 
paragraphs of SB-039, as follows, except you are not required to 
contact MDHI.
    (1) At intervals not to exceed 25 hours TIS, for inspection 
holes at L167 and R167, inspect the upper left and upper right 
attachment fittings, angles, and nutplates by following paragraphs 
2.B.(2) through 2.B.(4).
    (2) At intervals not to exceed 100 hours TIS, for inspection 
holes at L166 and R166, inspect the lower left and lower right 
attachment fittings, angles, and nutplates by following paragraphs 
2.B.(2) through 2.B.(4).
    (3) At intervals not to exceed 1200 hours TIS, for inspection 
holes L153 and R153 using a mirror or borescope, inspect the bottom 
surface of each longeron by following paragraphs 2.C.(2) and 
2.C.(3).
    (d) Before further flight, replace any cracked attachment 
fitting, angle, nutplate, longeron, and any nutplate with thread 
damage with an appropriate airworthy part.
    (e) On or before 4 years from the effective date of this AD, 
modify the aft fuselage to strengthen the tailboom attachments and 
the longerons by following the Accomplishment Instructions of MDHI 
Technical Bulletin TB600N-007, dated January 12, 2004 (TB-007). 
Modifying the aft fuselage by following TB-007 constitutes 
terminating action for the requirements of this AD.
    (f) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Los Angeles Aircraft Certification Office (LAACO), FAA, 
for information about previously approved alternative methods of 
compliance.


[[Page 7065]]


    Issued in Fort Worth, Texas, on February 2, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2608 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.