Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters, 38529-38532 [E7-13624]

Download as PDF jlentini on PROD1PC65 with PROPOSALS Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules (c) For Type 1 and Type 3 vertical fins, inspect the vertical fin and fin support bracket for paint, and the vertical fin attaching hardware for proper torque, in accordance with steps 5. and 6. of the Accomplishment Instructions of the ASB. (d) For Type 2 vertical fins, inspect the vertical fin and fin support bracket for paint, the vertical fin attaching hardware for proper torque, and the amount of gap between the vertical fin support bracket and the vertical fin doubler in accordance with steps 5., 6., and 7. of the Accomplishment Instructions of the ASB. (e) If the inspections required by paragraphs (c) and (d) of this AD indicate that the torque and gap are within limits, and there is no paint present, visually inspect the vertical fin support bracket in the area of the vertical fin attaching hardware for a crack using a 10x or higher power magnifying glass. (1) If no crack is found, re-torque the vertical fin attaching hardware to between 75 and 95 in. lbs. (8.47 to 10.75 Nm). (2) If a crack is found, replace the twopiece vertical fin support bracket with a onepiece vertical fin casting support, P/N 206– 033–426–003. (f) Based on your finding in paragraphs (c) and (d) of this AD, if either the torque or gap is out of limits, or paint is present: (1) Remove the vertical fin. (2) Remove all the primer and paint coatings in the areas indicated in Figure I of the ASB. (3) Fluorescent penetrant inspect (FPI) the vertical fin support. (4) If a crack is found, replace the twopiece vertical fin support with a one-piece vertical fin casting support, P/N 206–033– 426–003. (5) If no crack is found, apply two coats of Polyamide Epoxy Primer on bare metal surfaces. (g) For Type 2 vertical fins only: (1) If incorrect washers (spacers) or no washers are installed, visually inspect the 4 vertical fin potted inserts as depicted in the vertical fin detail in Figure I of the ASB for any damage using a 10x or higher power magnifying glass. (2) If any of the 4 vertical fin potted inserts is damaged with no other damage to the surrounding areas, remove and replace the damaged potted insert with an airworthy potted insert. (3) After assuring that all 4 installed vertical fin potted inserts are undamaged, install the correct washers in accordance with step 9.d. of the Accomplishment Instructions of the ASB. (h) This AD revises the helicopter maintenance manual by adding an inspection of the torque on the vertical fin attaching hardware, and inspections of the vertical fin and vertical fin support, to the 100-hour TIS and annual scheduled inspections. (i) 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 Manager, Regulations and Policy Group, FAA, ATTN: Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone VerDate Aug<31>2005 17:25 Jul 12, 2007 Jkt 211001 (817) 222–5122, fax (817) 222–5961, for information about previously approved alternative methods of compliance. Note: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF– 2006–12, dated June 5, 2006. Issued in Fort Worth, Texas, on July 3, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–13607 Filed 7–12–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28691; Directorate Identifier 2006–SW–22–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes superseding an existing airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters. That AD currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass, certain inspections of the lubrication pump (pump), and replacing the MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that before an MGB or pump with any hours time-in-service (TIS) can be installed, it must meet the AD requirements. This action would retain those requirements but would add all serial-numbered pumps to the applicability. This proposal is prompted by additional cases of MGB lubrication pump deterioration and a further investigation that determined that all serial-numbered pumps might be affected. The actions specified by the proposed AD are intended to detect sludge on the chip detector and dark oil in the MGB, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter. Comments must be received on or before September 11, 2007. DATES: PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 38529 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; • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays; or • Fax: 202–493–2251. • You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: ADDRESSES: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–28691, Directorate Identifier 2006–SW–22–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 rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the E:\FR\FM\13JYP1.SGM 13JYP1 38530 Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. jlentini on PROD1PC65 with PROPOSALS Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information 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 in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion On May 24, 2006, we issued AD 2003–21–09 R1, Amendment 39–14621 (71 FR 31070, June 1, 2006), to revise AD 2003–21–09. The revised AD required the same actions as AD 2003– 21–09 but limited the applicability to ECF helicopters with a pump, part number (P/N) 355A32–0700–01, with a serial number (S/N) 5731 or higher or with a S/N below 5731 if the pump has been overhauled or repaired after June 1, 1995. AD 2003–21–09 R1 was prompted by an investigation that revealed a malfunction occurred after modifying the pump case on certain pumps and after major overhaul and repairs. The requirements of that AD limited the applicability to certain pumps and were intended to detect sludge on the chip detector and dark oil in the MGB, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter. Since issuing that AD, ECF has issued Revision 1 to Alert Service Bulletin (ASB) No. 05.00.40, dated January 5, 2006, which adds pumps, P/N 355A32– 0700–01, with a S/N SAR 1, SAR 2, or SAR 5 to its effectivity. Also, Eurocopter has issued Emergency ASB No. 05.00.40, Revision 2, dated December 20, 2006, which supersedes the instructions in Revision 1 and extends the effectivity of these instructions to all serial-numbered pumps, P/N 355A32– 0700–01, 355A32–0700–02, and 355A32–0701–00. Revision 2 states that a further incident of MGB pump malfunction has been reported since the original four cases and shows that the machining modification of the earlier pumps is not the only reason for early deterioration of the oil pumps. The DGAC classified these ASBs as mandatory and issued AD No. F–2006– 027, Revision A, dated February 1, 2006, VerDate Aug<31>2005 16:43 Jul 12, 2007 Jkt 211001 and Emergency AD No. 2006–0378–E, effective December 27, 2006, which supersedes and cancels AD No. F–2006– 027. These helicopter models are manufactured in France and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type designs. Therefore, the proposed AD would supersede AD 2003–21–09 R1 and retain the requirements in that AD but would also require adding pumps, P/N 355A32–0700–01, 355A32–0700– 02, and 355A32–0701–00, any S/N, to the applicability. The FAA estimates that this proposed AD would affect 84 helicopters of U.S. registry, assuming they all have MGB pumps with applicable S/Ns. It would take about: • 10 minutes to check the chip detector and the MGB oil sight glass, • 4 work hours to remove the MGB and pump, • 1 work hour to inspect the pump, • 4 work hours to install a serviceable MGB and pump at an average labor rate of $80 per work hour, and • $4,000 for an overhauled pump and up to $60,000 for an overhauled MGB per helicopter. Based on these figures, we estimate the revised total cost impact of the AD on U.S. operators to be $355,920 per year, assuming replacement of one overhauled MGB and pump on one helicopter per year and a daily check on all helicopters for 260 days per year. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, 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; PO 00000 Frm 00035 Fmt 4702 Sfmt 4702 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 draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft economic evaluation. 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. § 39.13 [Amended] 2. Section 39.13 is amended by removing Amendment 39–14621 (71 FR 31070, June 1, 2006), and by adding a new airworthiness directive (AD), to read as follows: Eurocopter France: Docket No. FAA–2007– 28691; Directorate Identifier 2006–SW– 22–AD. Supersedes AD 2003–21–09 R1, Amendment 39–14621, Docket No. 2003–SW–10–AD. E:\FR\FM\13JYP1.SGM 13JYP1 Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules VerDate Aug<31>2005 16:43 Jul 12, 2007 Jkt 211001 this visual check and must enter compliance into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). ‘‘Sludge’’ is a deposit on the chip detector that is typically dark in color and in the form of a film or paste, as compared to metal chips or particles normally found on a chip detector. Sludge may have both metallic or nonmetallic properties, may consist of copper (pinion bearing), magnesium (pump case), and steel (pinion) from the oil pump, and a nonmetallic substance from the chemical breakdown of the oil as it interacts with the metal. (b) Before further flight, if any sludge is found on the chip detector, remove, open, and inspect the pump. (c) Before further flight, if the oil appears dark in color when it is observed through the MGB oil-sight glass, take an oil sample. If the PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 oil taken in the sample is dark or dark purple, before further flight, remove, open, and inspect the pump. Note 1: Eurocopter France Alert Service Bulletin (ASB) No. 05.00.40, Revision 1, dated January 5, 2006, and Emergency ASB No. 05.00.40, Revision 2, dated December 20, 2006, pertain to the subject of this AD. (d) While inspecting the pump, if you find any of the following, replace the MGB and the pump with an airworthy MGB and pump before further flight: (1) Crank pin play, (2) Out of round bronze bushing in area ‘‘A’’ of Figure 1 of this AD, (3) Offset of the driven gear pinion, (4) Metal chips, or (5) Wear in area ‘‘C’’ of Figure 1 of this AD. BILLING CODE 4910–13–P E:\FR\FM\13JYP1.SGM 13JYP1 EP13JY07.000</GPH> jlentini on PROD1PC65 with PROPOSALS Applicability: Model AS355E, F, F1, F2, and N helicopters, with a main gear box (MGB) lubrication pump (pump), part number (P/N) 355A32–0700–01, 355A32– 0700–02, or 355A32–0701–00, any serial number (S/N), certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect sludge on the chip detector and dark oil in the MGB, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter, do the following: (a) Before the first flight of each day and at intervals not to exceed 10 hours time-inservice (TIS), check the MGB magnetic chip detector plug (chip detector) for any sludge. Also, check for dark oil in the MGB oil-sight glass. An owner/operator (pilot) holding at least a private pilot certificate may perform 38531 38532 Federal Register / Vol. 72, No. 134 / Friday, July 13, 2007 / Proposed Rules Note 2: If wear is present in the B area only, as depicted in Figure 1, replacing the MGB and the pump is not required. (e) Before replacing an MGB with a pump to which this AD applies, accomplish the requirements of paragraphs (a), (b), and (c) 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 Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Ed Cuevas, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961, for information about previously approved alternative methods of compliance. Note 3: The subject of this AD is addressed in Direction Generale De L’Aviation Civile (France) AD No. F–2006–027, dated February 1, 2006, and Emergency AD No. 2006–0378– E, dated December 21, 2006. [Docket No. FAA–2007–28689; Directorate Identifier 2006–SW–17–AD] 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; • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays; or • Fax: (202) 493–2251. You may get the service information identified in this proposed AD from FreeFlight Systems, 3700 IH 35, Waco, Texas, USA, 76706, or by calling (254) 662–0000. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Sung-Hui Cavazos, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Special Certification Office, Fort Worth, Texas 76193–0170, telephone (817) 222–5142, fax (817) 222–5785. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Comments Invited Issued in Fort Worth, Texas, on July 2, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–13624 Filed 7–12–07; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Trimble or FreeFlight Systems 2101 I/O Approach Plus Global Positioning System (GPS) Navigation Systems Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). jlentini on PROD1PC65 with PROPOSALS AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the Trimble or FreeFlight Systems 2101 I/O Approach Plus global positioning system (GPS) navigation system (2101 I/O Approach Plus system). The AD would require a software upgrade for this system. This proposal is prompted by an incident that led to the discovery of several annunciation errors with the 2101 I/O Approach Plus system. The actions specified by the proposed AD are intended to prevent a pilot from making an unsafe decision based on erroneous information provided by the 2101 I/O Approach Plus system, which could result in loss of control of the aircraft. DATES: Comments must be received on or before September 11, 2007. VerDate Aug<31>2005 16:43 Jul 12, 2007 Jkt 211001 ADDRESSES: We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–28689, Directorate Identifier 2006–SW–17–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 rulemaking. Using the search function of our docket web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, PO 00000 Frm 00037 Fmt 4702 Sfmt 4702 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5527) is located in Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion This document proposes adopting a new AD for the 2101 I/O Approach Plus system that would require a software upgrade. This proposal is prompted by an incident involving a Federal Republic of Germany military helicopter that led to the discovery of the following system malfunctions: • Under certain conditions, when the system enters Dead Reckoning (DR) mode, the navigation and Super flags are removed from the display; however, the DR message and associated message light annunciation may fail to illuminate; • The navigation and Super flags may not be removed from the display as required during approach mode after loss of a Receiver Autonomous Integrity Monitor (RAIM) condition; and • When a RAIM error occurs (detects a satellite failure) and the system is unable to exclude the affected satellite, the unit may fail to enter DR mode and may fail to remove the navigation and Super flags from the display. These malfunctions could result in the following unsafe conditions: • System could fail when interfaced with Terrain Awareness Warning System (TAWS) and the TAWS can fail to annunciate terrain alerts; • System could provide misleading heading information; or • System may provide erroneous navigation fault annunciations. The actions specified by the proposed AD are intended to prevent a pilot from making an unsafe decision based on erroneous information provided by the 2101 I/O Approach Plus system, which could result in loss of control of the aircraft. These unsafe conditions are likely to exist or develop on any aircraft with a 2101 I/O Approach Plus system installed. Therefore, the proposed AD would require, within 180 days after the effective date of the AD for aircraft E:\FR\FM\13JYP1.SGM 13JYP1

Agencies

[Federal Register Volume 72, Number 134 (Friday, July 13, 2007)]
[Proposed Rules]
[Pages 38529-38532]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13624]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28691; Directorate Identifier 2006-SW-22-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS355E, F, F1, 
F2, and N Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes superseding an existing airworthiness 
directive (AD) for the specified Eurocopter France (ECF) helicopters. 
That AD currently requires certain checks of the magnetic chip detector 
plug (chip detector) and the main gearbox (MGB) oil-sight glass, 
certain inspections of the lubrication pump (pump), and replacing the 
MGB and the pump with an airworthy MGB and pump, if necessary. Also, 
the AD requires that before an MGB or pump with any hours time-in-
service (TIS) can be installed, it must meet the AD requirements. This 
action would retain those requirements but would add all serial-
numbered pumps to the applicability. This proposal is prompted by 
additional cases of MGB lubrication pump deterioration and a further 
investigation that determined that all serial-numbered pumps might be 
affected. The actions specified by the proposed AD are intended to 
detect sludge on the chip detector and dark oil in the MGB, to prevent 
failure of the MGB pump, seizure of the MGB, loss of drive to an engine 
and main rotor, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before September 11, 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;
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays; or
     Fax: 202-493-2251.
     You may get the service information identified in this 
proposed AD from American Eurocopter Corporation, 2701 Forum Drive, 
Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 
641-3527.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-
28691, Directorate Identifier 2006-SW-22-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 rulemaking. Using the search 
function of our docket Web site, you can find and read the comments to 
any of our dockets, including the name of the individual who sent or 
signed the comment. You may review the DOT's complete Privacy Act 
Statement in the

[[Page 38530]]

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 docket that contains the proposed AD, any 
comments, and other information 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 in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    On May 24, 2006, we issued AD 2003-21-09 R1, Amendment 39-14621 (71 
FR 31070, June 1, 2006), to revise AD 2003-21-09. The revised AD 
required the same actions as AD 2003-21-09 but limited the 
applicability to ECF helicopters with a pump, part number (P/N) 355A32-
0700-01, with a serial number (S/N) 5731 or higher or with a S/N below 
5731 if the pump has been overhauled or repaired after June 1, 1995. AD 
2003-21-09 R1 was prompted by an investigation that revealed a 
malfunction occurred after modifying the pump case on certain pumps and 
after major overhaul and repairs. The requirements of that AD limited 
the applicability to certain pumps and were intended to detect sludge 
on the chip detector and dark oil in the MGB, to prevent failure of the 
MGB pump, seizure of the MGB, loss of drive to an engine and main 
rotor, and subsequent loss of control of the helicopter.
    Since issuing that AD, ECF has issued Revision 1 to Alert Service 
Bulletin (ASB) No. 05.00.40, dated January 5, 2006, which adds pumps, 
P/N 355A32-0700-01, with a S/N SAR 1, SAR 2, or SAR 5 to its 
effectivity. Also, Eurocopter has issued Emergency ASB No. 05.00.40, 
Revision 2, dated December 20, 2006, which supersedes the instructions 
in Revision 1 and extends the effectivity of these instructions to all 
serial-numbered pumps, P/N 355A32-0700-01, 355A32-0700-02, and 355A32-
0701-00. Revision 2 states that a further incident of MGB pump 
malfunction has been reported since the original four cases and shows 
that the machining modification of the earlier pumps is not the only 
reason for early deterioration of the oil pumps. The DGAC classified 
these ASBs as mandatory and issued AD No. F-2006-027, Revision A, dated 
February 1, 2006, and Emergency AD No. 2006-0378-E, effective December 
27, 2006, which supersedes and cancels AD No. F-2006-027.
    These helicopter models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, the DGAC has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
DGAC, reviewed all available information, and determined that AD action 
is necessary for products of these type designs that are certificated 
for operation in the United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type designs. Therefore, the 
proposed AD would supersede AD 2003-21-09 R1 and retain the 
requirements in that AD but would also require adding pumps, P/N 
355A32-0700-01, 355A32-0700-02, and 355A32-0701-00, any S/N, to the 
applicability.
    The FAA estimates that this proposed AD would affect 84 helicopters 
of U.S. registry, assuming they all have MGB pumps with applicable S/
Ns. It would take about:
     10 minutes to check the chip detector and the MGB oil 
sight glass,
     4 work hours to remove the MGB and pump,
     1 work hour to inspect the pump,
     4 work hours to install a serviceable MGB and pump at an 
average labor rate of $80 per work hour, and
     $4,000 for an overhauled pump and up to $60,000 for an 
overhauled MGB per helicopter.
    Based on these figures, we estimate the revised total cost impact 
of the AD on U.S. operators to be $355,920 per year, assuming 
replacement of one overhauled MGB and pump on one helicopter per year 
and a daily check on all helicopters for 260 days per year.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, 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 draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft economic 
evaluation.

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 39-14621 (71 FR 
31070, June 1, 2006), and by adding a new airworthiness directive (AD), 
to read as follows:

Eurocopter France: Docket No. FAA-2007-28691; Directorate Identifier 
2006-SW-22-AD. Supersedes AD 2003-21-09 R1, Amendment 39-14621, 
Docket No. 2003-SW-10-AD.


[[Page 38531]]


    Applicability: Model AS355E, F, F1, F2, and N helicopters, with 
a main gear box (MGB) lubrication pump (pump), part number (P/N) 
355A32-0700-01, 355A32-0700-02, or 355A32-0701-00, any serial number 
(S/N), certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect sludge on the chip detector and dark oil in the MGB, 
to prevent failure of the MGB pump, seizure of the MGB, loss of 
drive to an engine and main rotor, and subsequent loss of control of 
the helicopter, do the following:
    (a) Before the first flight of each day and at intervals not to 
exceed 10 hours time-in-service (TIS), check the MGB magnetic chip 
detector plug (chip detector) for any sludge. Also, check for dark 
oil in the MGB oil-sight glass. An owner/operator (pilot) holding at 
least a private pilot certificate may perform this visual check and 
must enter compliance into the aircraft maintenance records in 
accordance with 14 CFR 43.11 and 91.417(a)(2)(v). ``Sludge'' is a 
deposit on the chip detector that is typically dark in color and in 
the form of a film or paste, as compared to metal chips or particles 
normally found on a chip detector. Sludge may have both metallic or 
nonmetallic properties, may consist of copper (pinion bearing), 
magnesium (pump case), and steel (pinion) from the oil pump, and a 
nonmetallic substance from the chemical breakdown of the oil as it 
interacts with the metal.
    (b) Before further flight, if any sludge is found on the chip 
detector, remove, open, and inspect the pump.
    (c) Before further flight, if the oil appears dark in color when 
it is observed through the MGB oil-sight glass, take an oil sample. 
If the oil taken in the sample is dark or dark purple, before 
further flight, remove, open, and inspect the pump.

    Note 1: Eurocopter France Alert Service Bulletin (ASB) No. 
05.00.40, Revision 1, dated January 5, 2006, and Emergency ASB No. 
05.00.40, Revision 2, dated December 20, 2006, pertain to the 
subject of this AD.

    (d) While inspecting the pump, if you find any of the following, 
replace the MGB and the pump with an airworthy MGB and pump before 
further flight:
    (1) Crank pin play,
    (2) Out of round bronze bushing in area ``A'' of Figure 1 of 
this AD,
    (3) Offset of the driven gear pinion,
    (4) Metal chips, or
    (5) Wear in area ``C'' of Figure 1 of this AD.

BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP13JY07.000



[[Page 38532]]


    Note 2: If wear is present in the B area only, as depicted in 
Figure 1, replacing the MGB and the pump is not required.

    (e) Before replacing an MGB with a pump to which this AD 
applies, accomplish the requirements of paragraphs (a), (b), and (c) 
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 Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: Ed Cuevas, Fort Worth, Texas 76193-0111, 
telephone (817) 222-5355, fax (817) 222-5961, for information about 
previously approved alternative methods of compliance.

    Note 3: The subject of this AD is addressed in Direction 
Generale De L'Aviation Civile (France) AD No. F-2006-027, dated 
February 1, 2006, and Emergency AD No. 2006-0378-E, dated December 
21, 2006.


    Issued in Fort Worth, Texas, on July 2, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-13624 Filed 7-12-07; 8:45 am]
BILLING CODE 4910-13-C
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