Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters, 36821-36823 [E8-14723]

Download as PDF Federal Register / Vol. 73, No. 126 / Monday, June 30, 2008 / Proposed Rules Reason DEPARTMENT OF TRANSPORTATION (d) European Aviation Safety Agency (EASA) AD No. 2008–0033, dated February 19, 2008, states: A number of propeller blade outer sleeves have been found with cracks since 1996. Testing has shown that blade retention integrity is not affected by this cracking. However, this condition, if not detected and corrected, can lead to blade counterweight release, possibly resulting in damage to the aircraft and injury to occupants or persons on the ground. This AD requires initial and repetitive visual inspections of propeller blade root outer sleeves for cracks, and removal before further flight of propeller blades with cracked blade root outer sleeves. We are issuing this AD to prevent blade counterweight release, which could result in injury or damage to the airplane. Actions and Compliance (e) Unless already done, do the following actions. Propeller Blade Outer Sleeve Visual Inspections (1) At the next 1,600 flight hours (FH) aircraft check after the effective date of this AD, or, after any blade accumulates 15,000 FH time-in-service, whichever occurs later, visually inspect all propeller blade root outer sleeves for cracks. (2) Thereafter, at intervals not to exceed 1,600 FH, visually inspect all propeller blade root outer sleeves for cracks. (3) Before further flight, remove any propeller blades found cracked during the visual inspections in paragraphs (e)(1) and (e)(2) of this AD. FAA AD Differences (f) None. (g) Alternative Methods of Compliance (AMOCs): The Manager, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information dwashington3 on PRODPC61 with PROPOSALS (h) Refer to European Aviation Safety Agency AD 2008–0033, dated February 19, 2008, and Dowty Propellers Alert Service Bulletin No. SF340–61–A106, dated December 5, 2007, for related information. (i) Contact Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: terrance.fahr@faa.gov; telephone (781) 238–7155; fax (781) 238– 7170, for more information about this AD. Issued in Burlington, Massachusetts, on June 24, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–14715 Filed 6–27–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:21 Jun 27, 2008 Jkt 214001 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: Supplemental notice of proposed rulemaking; reopening of comment period. AGENCY: This document revises an earlier proposed superseding airworthiness directive (AD) for the specified Eurocopter France (ECF) model 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 a pump or MGB with any hours time-in-service (TIS) can be installed, it must meet the AD requirements. The earlier proposed superseding AD proposed retaining those requirements but proposed adding all serial-numbered pumps to the applicability. This supplemental proposal is prompted by an improved procedure for detecting oil pump wear earlier and is considered more accurate than the procedure proposed previously. The actions specified by the proposed AD are intended to implement improved procedures to detect a failing MGB oil pump, 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. SUMMARY: Comments must be received on or before August 29, 2008. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room DATES: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 36821 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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. 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:// www.regulations.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 the 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, 2000 (65 FR 19477–78). 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 receipt. Discussion A proposal to amend 14 CFR part 39 to add an AD for the specified ECF E:\FR\FM\30JNP1.SGM 30JNP1 dwashington3 on PRODPC61 with PROPOSALS 36822 Federal Register / Vol. 73, No. 126 / Monday, June 30, 2008 / Proposed Rules model helicopters was published in the Federal Register on July 13, 2007 (72 FR 38529). That Notice of Proposed Rulemaking (NPRM) proposed superseding AD 2003–21–09 R1, Amendment 39–14621, (71 FR 31070, June 1, 2006) by retaining the requirements in that AD and adding pumps, P/N 355A32–0700–01, 355A32– 0700–02, and 355A32–0701–00, any S/ N, to the applicability. That NPRM was prompted by additional cases of MGB lubrication pump deterioration and a further investigation that determined that all serial-numbered pumps might be affected. This condition, if not corrected, could result in 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 NPRM, the manufacturer has developed an improved procedure for monitoring the condition of the MGB lubrication pump. Eurocopter has issued an Alert Service Bulletin No. 05.00.51, dated July 9, 2007 (ASB), specifying the improved procedure. The European Aviation Safety Agency (EASA), the Technical Agent for the Member States of the European Community, has issued EASA Emergency AD No. 2007–0209E, dated August 6, 2007, in response to the ASB. Also, we received comments from one commenter to the NPRM. The commenter agrees that the improved procedure, described in the ASB, is a better way to detect MGB oil pump problems because ‘‘sludge on the chip plug can come from sources within the MGB oil system.’’ The FAA agrees with the commenter that the improved procedure described in the ASB is a better way to detect MGB oil pump problems because this process reflects the progressive inefficiency as the oil pump wears as it relates to steady oil temperature and variable outside air temperature (OAT). Therefore, we are proposing to require the improved procedure for monitoring the condition of the MGB lubrication pump in lieu of checking the chip detector and oil-sight glass after an initial 25 hours TIS. Since this change expands the scope of the originally proposed rule, the FAA has determined that it is necessary to reopen the comment period to provide additional opportunity for public comment. We estimate that this proposed AD would affect 80 helicopters of U.S. registry, and the proposed actions would take about: • 15 minutes to perform the procedures to check the condition of the MGB oil and chip detector plug, VerDate Aug<31>2005 15:21 Jun 27, 2008 Jkt 214001 • 4 work hours to remove the MGB and pump, • 1 work hour to inspect the pump under the 10-hour, 25-hour, and 110hour TIS procedures, • 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 total cost impact of the proposed AD on U.S. operators to be $107,040 per year, assuming (a) one overhauled MGB and pump would be replaced on one helicopter per year, (b) all 80 helicopters would operate for 10 days undergoing 10 daily checks and 2 10-hour TIS inspections, and (c) each of the 80 helicopters operate for 260 hours per year with 20 helicopters receiving the repetitive 25-hour TIS inspection or 10.4 inspections per helicopter per year (260/25) for a total of 208 inspections (20 * 10.4) and 60 helicopters receiving the repetitive 110-hour TIS inspection or 2.36 inspections per helicopter per year (260/110) for a total of 142 inspections (60 * 2.36). 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. 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 AD docket to examine the draft economic evaluation. 1. The authority citation for part 39 continues to read as follows: 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. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive 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. 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. 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 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 E:\FR\FM\30JNP1.SGM 30JNP1 dwashington3 on PRODPC61 with PROPOSALS Federal Register / Vol. 73, No. 126 / Monday, June 30, 2008 / Proposed Rules 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 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) Within 25 hours TIS, unless accomplished previously, after operating both engines at normal operating revolutions per minute (RPM) for at least 20 minutes to ensure the MGB oil temperature has stabilized, inspect the oil pump for wear by following the Accomplishment Instructions, paragraph 2.B.2., steps 1. through 6., of Eurocopter Alert Service Bulletin No. 05.00.51, dated July 9, 2007 (ASB). This AD does not require you to send the information to the manufacturer. (1) Record the outside air temperature (OAT) and rotor speed (NR RPM) and plot the point at which they intersect using the graph in Figure 1 or 2 of the ASB. (2) If the point on the graph at the intersection of the recorded OAT and the NR RPM falls within: (i) Zone 3—Before further flight, replace the MGB and pump with an airworthy MGB and pump. (ii) Zone 2—At intervals not to exceed 25 hours TIS, repeat the inspection procedures by following the Accomplishment Instructions, paragraph 2.B.2, steps 1 through 6, of the ASB. After being classified in ‘‘Zone 2,’’ you must obtain two successive inspections separated by at least 24 hours TIS that fall within Zone 1 before you can begin to inspect at intervals not to exceed 110 hours TIS by following paragraph (d)(2)(iii) of this AD for Zone 1. Note 2: In addition to a worn oil pump, the loss of oil pressure could also be due to a clogged oil filter or cooler, a pinched hose, or an inaccurate pressure switch. (iii) Zone 1—At intervals not to exceed 110 hours TIS, repeat the inspection procedures by following the Accomplishment Instructions, paragraph 2.B.2., steps 1 through 6, of the ASB. (3) Compliance with paragraphs (d)(1) and (d)(2) of this AD constitutes terminating action for the checks and inspections required by paragraphs (a), (b), and (c) of this AD. (e) 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, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, Rotorcraft Directorate, Fort Worth, Texas 76193–0111, VerDate Aug<31>2005 15:21 Jun 27, 2008 Jkt 214001 telephone (817) 222–5355, fax (817) 222– 5961. Note 3: The subject of this AD is addressed in European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, Emergency AD No. 2006–0378–E, dated December 21, 2006, and AD No. 2007–0209E, dated August 6, 2007. Issued in Fort Worth, Texas, on June 19, 2008. Judy I. Carl, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–14723 Filed 6–27–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF LABOR Occupational Safety and Health Administration 29 CFR Parts 1910 and 1915 [Docket No. OSHA–S049–2006–0675 (formerly OSHA Docket No. S–049)] RIN 1218–AB50 General Working Conditions in Shipyard Employment Occupational Safety and Health Administration (OSHA), Department of Labor. ACTION: Proposed rule; notice of informal public hearings. AGENCY: SUMMARY: OSHA is scheduling informal public hearings on the proposed rule on general working conditions in shipyard employment. DATES: Informal public hearings: The hearings will begin at 9:30 a.m., on the following dates: • September 9, 2008, in Washington, DC; and • October 21, 2008, in Seattle, WA. If necessary, the hearing will continue at the same time on subsequent days at each location. Notice of intention to appear at the hearing: Interested persons who intend to present testimony or question witnesses at either the Washington, DC, or Seattle, WA, hearing must submit (transmit, send, postmark, deliver) a notice of their intention to do so by July 18, 2008. Hearing testimony and documentary evidence: Interested persons who request more than 10 minutes to present testimony or who intend to submit documentary evidence at the hearing must submit (transmit, send, postmark, deliver) the full text of their testimony and all documentary evidence by August 8, 2008. ADDRESSES: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 36823 Informal public hearings: The Washington, DC, hearing will be held in the auditorium of the U.S. Department of Labor, 200 Constitution Avenue, NW., Washington, DC 20210. OSHA will announce the address of the Seattle, WA, hearing in a later Federal Register document. Notice of intention to appear, hearing testimony and documentary evidence: You may submit (transmit, send, postmark, deliver) your notice of intention to appear, hearing testimony, and documentary evidence, identified by docket number OSHA–S049–2006– 0675, by any of the following methods: • Federal eRulemaking Portal: https:// www.regulations.gov. Follow the instructions online for electronically submitting materials, including attachments; • Fax: If your written submission does not exceed 10 pages, including attachments, you may fax it to the OSHA Docket Office at (202) 693–1648; or • Regular mail, express delivery, hand delivery, and messenger and courier service: Submit your materials to the OSHA Docket Office, Docket No. OSHA–S049–2006–0675, U.S. Department of Labor, Room N–2625, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–2350 (TTY number (877) 889– 5627). Deliveries (express mail, hand delivery, and messenger and courier service) are accepted during the Department of Labor’s and OSHA Docket Office’s normal hours of operation, 8:15 a.m. to 4:45 p.m., e.t. Instructions: All submissions must include the Agency name and docket number for this rulemaking (Docket No. OSHA–S049–2006–0675). All submissions, including any personal information, are placed in the public docket without change and may be available online at https:// www.regulations.gov. Therefore, OSHA cautions you about submitting certain personal information such as social security numbers and birthdates. Because of security-related procedures, the use of regular mail may cause a significant delay in the receipt of your submissions. For information about security-related procedures for submitting materials by express delivery, hand delivery, messenger, or courier service, please contact the OSHA Docket Office. For additional information on submitting notices of intention to appear, hearing testimony or documentary evidence, see the SUPPLEMENTARY INFORMATION section of this notice. Docket: To read or download background documents as well as E:\FR\FM\30JNP1.SGM 30JNP1

Agencies

[Federal Register Volume 73, Number 126 (Monday, June 30, 2008)]
[Proposed Rules]
[Pages 36821-36823]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14723]


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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: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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

SUMMARY: This document revises an earlier proposed superseding 
airworthiness directive (AD) for the specified Eurocopter France (ECF) 
model 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 a pump or MGB with any 
hours time-in-service (TIS) can be installed, it must meet the AD 
requirements. The earlier proposed superseding AD proposed retaining 
those requirements but proposed adding all serial-numbered pumps to the 
applicability. This supplemental proposal is prompted by an improved 
procedure for detecting oil pump wear earlier and is considered more 
accurate than the procedure proposed previously. The actions specified 
by the proposed AD are intended to implement improved procedures to 
detect a failing MGB oil pump, 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 August 29, 2008.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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.

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://
www.regulations.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 the 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, 
2000 (65 FR 19477-78).

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 receipt.

Discussion

    A proposal to amend 14 CFR part 39 to add an AD for the specified 
ECF

[[Page 36822]]

model helicopters was published in the Federal Register on July 13, 
2007 (72 FR 38529). That Notice of Proposed Rulemaking (NPRM) proposed 
superseding AD 2003-21-09 R1, Amendment 39-14621, (71 FR 31070, June 1, 
2006) by retaining the requirements in that AD and adding pumps, P/N 
355A32-0700-01, 355A32-0700-02, and 355A32-0701-00, any S/N, to the 
applicability. That NPRM was prompted by additional cases of MGB 
lubrication pump deterioration and a further investigation that 
determined that all serial-numbered pumps might be affected. This 
condition, if not corrected, could result in 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 NPRM, the manufacturer has developed an improved 
procedure for monitoring the condition of the MGB lubrication pump. 
Eurocopter has issued an Alert Service Bulletin No. 05.00.51, dated 
July 9, 2007 (ASB), specifying the improved procedure. The European 
Aviation Safety Agency (EASA), the Technical Agent for the Member 
States of the European Community, has issued EASA Emergency AD No. 
2007-0209E, dated August 6, 2007, in response to the ASB. Also, we 
received comments from one commenter to the NPRM. The commenter agrees 
that the improved procedure, described in the ASB, is a better way to 
detect MGB oil pump problems because ``sludge on the chip plug can come 
from sources within the MGB oil system.''
    The FAA agrees with the commenter that the improved procedure 
described in the ASB is a better way to detect MGB oil pump problems 
because this process reflects the progressive inefficiency as the oil 
pump wears as it relates to steady oil temperature and variable outside 
air temperature (OAT). Therefore, we are proposing to require the 
improved procedure for monitoring the condition of the MGB lubrication 
pump in lieu of checking the chip detector and oil-sight glass after an 
initial 25 hours TIS.
    Since this change expands the scope of the originally proposed 
rule, the FAA has determined that it is necessary to reopen the comment 
period to provide additional opportunity for public comment.
    We estimate that this proposed AD would affect 80 helicopters of 
U.S. registry, and the proposed actions would take about:
     15 minutes to perform the procedures to check the 
condition of the MGB oil and chip detector plug,
     4 work hours to remove the MGB and pump,
     1 work hour to inspect the pump under the 10-hour, 25-
hour, and 110-hour TIS procedures,
     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 total cost impact of the 
proposed AD on U.S. operators to be $107,040 per year, assuming (a) one 
overhauled MGB and pump would be replaced on one helicopter per year, 
(b) all 80 helicopters would operate for 10 days undergoing 10 daily 
checks and 2 10-hour TIS inspections, and (c) each of the 80 
helicopters operate for 260 hours per year with 20 helicopters 
receiving the repetitive 25-hour TIS inspection or 10.4 inspections per 
helicopter per year (260/25) for a total of 208 inspections (20 * 10.4) 
and 60 helicopters receiving the repetitive 110-hour TIS inspection or 
2.36 inspections per helicopter per year (260/110) for a total of 142 
inspections (60 * 2.36).

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 AD docket 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 adding a new airworthiness directive 
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.

    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.
    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

[[Page 36823]]

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 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) Within 25 hours TIS, unless accomplished previously, after 
operating both engines at normal operating revolutions per minute 
(RPM) for at least 20 minutes to ensure the MGB oil temperature has 
stabilized, inspect the oil pump for wear by following the 
Accomplishment Instructions, paragraph 2.B.2., steps 1. through 6., 
of Eurocopter Alert Service Bulletin No. 05.00.51, dated July 9, 
2007 (ASB). This AD does not require you to send the information to 
the manufacturer.
    (1) Record the outside air temperature (OAT) and rotor speed (NR 
RPM) and plot the point at which they intersect using the graph in 
Figure 1 or 2 of the ASB.
    (2) If the point on the graph at the intersection of the 
recorded OAT and the NR RPM falls within:
    (i) Zone 3--Before further flight, replace the MGB and pump with 
an airworthy MGB and pump.
    (ii) Zone 2--At intervals not to exceed 25 hours TIS, repeat the 
inspection procedures by following the Accomplishment Instructions, 
paragraph 2.B.2, steps 1 through 6, of the ASB. After being 
classified in ``Zone 2,'' you must obtain two successive inspections 
separated by at least 24 hours TIS that fall within Zone 1 before 
you can begin to inspect at intervals not to exceed 110 hours TIS by 
following paragraph (d)(2)(iii) of this AD for Zone 1.

    Note 2: In addition to a worn oil pump, the loss of oil pressure 
could also be due to a clogged oil filter or cooler, a pinched hose, 
or an inaccurate pressure switch.

    (iii) Zone 1--At intervals not to exceed 110 hours TIS, repeat 
the inspection procedures by following the Accomplishment 
Instructions, paragraph 2.B.2., steps 1 through 6, of the ASB.
    (3) Compliance with paragraphs (d)(1) and (d)(2) of this AD 
constitutes terminating action for the checks and inspections 
required by paragraphs (a), (b), and (c) of this AD.
    (e) 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, FAA, ATTN: Ed Cuevas, 
Aviation Safety Engineer, Rotorcraft Directorate, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

    Note 3: The subject of this AD is addressed in European Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Community, Emergency AD No. 2006-0378-E, 
dated December 21, 2006, and AD No. 2007-0209E, dated August 6, 
2007.


    Issued in Fort Worth, Texas, on June 19, 2008.
Judy I. Carl,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-14723 Filed 6-27-08; 8:45 am]
BILLING CODE 4910-13-P
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