[Federal Register Volume 67, Number 94 (Wednesday, May 15, 2002)]
[Rules and Regulations]
[Pages 34598-34602]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-12051]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-SW-39-AD; Amendment 39-12751; AD 2002-10-05]
RIN 2120-AA64


Airworthiness Directives; MD Helicopters Inc. Model MD-900 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to MD Helicopters Inc. Model MD-900 helicopters, that 
currently requires inspecting the main rotor upper hub (hub) assembly 
drive plate attachment flange (flange), determining the torque of each 
flange nut (nut), and if a crack is found, before further flight, 
replacing the hub assembly. In addition to the current requirements, 
this action requires visually inspecting the outer surface of the 
flange at specified intervals, removing the drive plate and visually 
inspecting the flange for a crack at specified intervals, and replacing 
any unairworthy hub assembly. This amendment is prompted by reports 
that cracks starting at the drive plate attachment holes were found in 
the hub. The actions specified by this AD are intended to detect a 
crack in the flange and to prevent failure of the hub assembly, loss of 
drive to the main rotor, and subsequent loss of control of the 
helicopter.

DATES: Effective June 19, 2002.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of May 1, 2001 (66 FR 19383, April 16, 2001).

ADDRESSES: The service information referenced in this AD may be 
obtained from MD Helicopters Inc., Attn: Customer Support Division, 
4555 E. McDowell Rd., Mail Stop M615-GO48, Mesa, Arizona 85215-9734, 
telephone 1-800-388-3378, fax (480) 891-6782, or on the Web at 
www.mdhelicopters.com. This information may be examined at the FAA, 
Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., 
Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aviation Safety Engineer, 
FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 
Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5322, 
fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 by 
superseding AD 2001-07-09, Amendment 39-12175 (66 FR 19383, April 16, 
2001), for MD Helicopters Inc. Model MD-900 helicopters, was published 
in the Federal Register on December 17, 2001 (66 FR 64931). That action 
proposed to require inspecting the flange, determining the torque of 
each nut, and if a crack is found, before further flight, replacing the 
hub assembly. That action also proposed to require visually inspecting 
the outer surface of the flange at specified intervals, removing the 
drive plate and visually inspecting the flange for a crack at specified 
intervals, and replacing any unairworthy hub assembly.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of

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the cost to the public. The FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed with the 
exception of minor editorial changes. These changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates 28 helicopters of U.S. registry will be affected 
by this AD. It will take approximately:
     1 work hour per helicopter to verify the torque,
     3 work hours per helicopter to perform the inspection,
     10 work hours per helicopter to replace the hub assembly,
     1 work hour for a 100-hour TIS inspection, and
     3 work hours for a 300-hour TIS inspection.
    The average labor rate is $60 per work hour. Required parts to 
replace the hub assembly, if necessary, will cost approximately $21,610 
per helicopter. Based on these figures, the total cost impact of the AD 
on U.S. operators is estimated to be $159,770 for the first year, 
assuming 5 hub assembly replacements and assuming each helicopter has 6 
torque verifications, 6 inspections, two 100-hour inspections, and one 
300-hour inspection.
    The regulations adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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 39-12175 (66 FR 
19383, April 16, 2001), and by adding a new airworthiness directive 
(AD), Amendment 39-12751, to read as follows:


2002-10-05 MD Helicopters, Inc.: Amendment 39-12751. Docket No. 
2001-SW-39-AD. Supersedes AD 2001-07-09, Amendment 39-12175, Docket 
No. 2000-SW-15-AD.

    Applicability: Model MD-900 helicopters, with main rotor upper 
hub (hub) assembly, part number (P/N) 900R2101006-105 or P/N 
900R2101006-107, installed, certificated in any category.

    Note 1: This AD applies to each helicopter identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For helicopters that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the hub assembly, loss of drive to the 
main rotor, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) For the hub assembly, P/N 900R2101006-107:
    (1) Within 6 hours time-in-service (TIS), visually inspect the 
hub assembly drive plate attach flange (flange) for a crack and 
determine the torque of each flange attach nut (nut) in accordance 
with the Accomplishment Instructions, Part I, paragraph 2.A., steps 
(1) through (7) of MD Helicopter Inc. Service Bulletin SB900-072, 
dated December 10, 1999 (SB). If a crack is found, before further 
flight, remove and replace the hub assembly with an airworthy hub 
assembly.
    (2) Within 25 hours TIS, accomplish Part II, of the 
Accomplishment Instructions, paragraph 2.B., steps (1) through (6), 
(8), and (9) of the SB. If a crack is found, before further flight, 
remove and replace the hub assembly with an airworthy hub assembly.
    (b) For the hub assembly, P/N 900R2101006-105:
    (1) Within 6 hours TIS, visually inspect the flange for a crack 
and determine the torque of each nut in accordance with the 
Accomplishment Instructions, Part I, paragraph 2.A., steps (1) 
through (7) of the SB.

    Note 2: The SB effectivity does not include hub assembly, P/N 
900R2101006-105; however, certain provisions of this AD do apply to 
this P/N.

    (2) If any nut has less than 180 inch pounds (20.34 Nm) of 
torque, before further flight, remove the drive plate and fretting 
buffer and inspect the flange in accordance with the procedures in 
paragraph (b)(3) of this AD. If a crack is detected, before further 
flight, remove and replace the hub assembly with an airworthy hub 
assembly. Reassemble in accordance with the procedures in paragraph 
(b)(3) of this AD.
    (3) Within 25 hours TIS, remove the main rotor drive plate 
assembly and anti-fretting ring and visually inspect the hub 
assembly as follows:
    (i) If present, remove sealant from the drive plate attachment 
to the hub assembly.
    (ii) Mark the main rotor hub holes to correspond with the drive 
plate hole numbers (see Figure 1 of this AD).
    (iii) Remove the main rotor drive plate (drive plate) assembly 
and anti-fretting ring (fretting buffer).
    (iv) Inspect drive plate to hub assembly mating surfaces and the 
fretting buffer for fretting.
    (v) Using paint stripper (Consumable Item List C313 or 
equivalent) and cleaning solvent (C420 or equivalent), remove the 
paint from the upper mating surface of the hub assembly to enable an 
accurate visual inspection of each drive plate attachment bolt hole 
(bolt hole) area for cracking (Figure 1). Ensure the paint stripper 
and solvent DO NOT contaminate the upper bearing and upper grease 
seal areas.
    (vi) Using a 10x or higher magnifying glass and light, inspect 
the mating surface area and the area around and inside the 10 bolt 
holes of the hub assembly for a crack. If a crack is found, before 
further flight, replace the hub assembly with an airworthy hub 
assembly.
    (vii) If no crack is found, remove fretting debris from the 
mating surfaces of the hub assembly and the drive plate assembly, 
reassemble, fillet seal (C211 or equivalent) the surface of the 
drive plate to fretting buffer to hub assembly mating lines, and 
seal all exposed unpainted upper surfaces of the hub assembly.
    (viii) Reinstall the main rotor drive plate using 10 new sets of 
replacement attachment hardware. Torque the nuts to 160 inch pounds 
above locknut locking/run-on torque in the sequence shown (Figure 
1). Record in the rotorcraft logbook, or equivalent record, the 
locknut locking/run-on torque for each nut.
    (ix) After the next flight, verify that the torque on each of 
the 10 nuts is at least 160 inch-pounds above the locknut locking/
run-on torque (minimum torque). Re-torque as required without 
loosening nuts.
    (x) Thereafter, at intervals of at least 4 hours TIS, not to 
exceed 6 hours TIS, verify

[[Page 34600]]

that the torque of each of the 10 nuts is at least the minimum 
torque. Re-torque as required without loosening nuts. This torque 
verification is no longer required after the torque on each of the 
10 nuts has stabilized at a torque value of 160 or more inch-pounds 
for each nut during two successive torque verifications.
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[GRAPHIC] [TIFF OMITTED] TR15MY02.040

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    (c) Within 100 hours TIS and thereafter at intervals not to exceed 
100 hours TIS, visually inspect the outer surface of the flange for a 
crack using a light and a 10x or higher magnifying glass. If a crack is 
detected, replace the unairworthy hub assembly with an airworthy hub 
assembly before further flight.
    (d) At intervals not to exceed 300 hours TIS, remove the drive 
plate and visually inspect the flange for a crack using a light and a 
10x or higher magnifying glass. If a crack is detected, replace the 
unairworthy hub assembly with an airworthy hub assembly before further 
flight.
    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be used 
if approved by the Manager, Los Angeles Aircraft Certification Office 
(LAACO), FAA. Operators shall submit their requests through an FAA 
Principal Maintenance Inspector, who may concur or comment and then 
send it to the Manager, LAACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the LAACO.

    (f) If any nut torque is below minimum torque and no hub assembly 
crack is found before disassembly inspection, after re-torque in 
accordance with the applicable maintenance manual, a special flight 
permit for one flight below 100 knots indicated airspeed may be issued 
in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter 
to a location where the requirements of this AD can be accomplished.
    (g) The inspections and replacement, if necessary, shall be done in 
accordance with the Accomplishment Instructions, Part I, paragraph 
2.A., steps (1) through (7); and Part II, paragraph 2.B., steps (1) 
through (6), (8), and (9), of MD Helicopter Inc. Service Bulletin 
SB900-072, dated December 10, 1999. The incorporation by reference of 
that document was previously approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of May 
1, 2001 (66 FR 19383, April 16, 2001). Copies may be obtained from MD 
Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell 
Rd., Mail Stop M615-GO48, Mesa, Arizona 85215-9734, telephone 1-800-
388-3378, fax (480) 891-6782, or on the web at www.mdhelicopters.com. 
Copies may be inspected at the FAA, Office of the Regional Counsel, 
Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (h) This amendment becomes effective on June 19, 2002.

    Issued in Fort Worth, Texas, on May 2, 2002.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 02-12051 Filed 5-14-02; 8:45 am]
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