Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations 6451

Effective Date

(f) This amendment becomes effective on

February 6, 2001.

Issued in Renton, Washington, on January

9, 2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–1234 Filed 1–19–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–63–AD; Amendment

39–12083; AD 2000–25–52]

RIN 2120–AA64

Airworthiness Directives; MD

Helicopters, Inc. Model 369A, H, HE,

HM, HS, D, E, FF, and 500N Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Emergency Airworthiness

Directive (AD) 2000–25–52 which was

sent previously to all known U.S.

owners and operators of MD

Helicopters, Inc. (MDHI) Model 369A,

H, HE, HM, HS, D, E, FF, and 500N

helicopters. This amendment

supersedes an existing emergency AD

that requires, before further flight,

performing a tap inspection on both the

upper and lower surfaces of each main

rotor blade (blade). If any voids are

detected that exceed specified

inspection requirements, the emergency

AD also requires replacing the

unairworthy blade with an airworthy

blade before further flight. This

amendment requires the same actions as

the emergency AD and corrects the

applicability to include the appropriate

serial numbers. This amendment is

prompted by the discovery of an error

in the emergency AD. The actions

specified by this AD are intended to

prevent failure of a blade and

subsequent loss of control of the

helicopter.

DATES: Effective February 6, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 6,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

March 23, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

63–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.

The service information referenced in

this AD may be obtained from

Helicopter Technology Company, LLC,

12923 South Spring St., Los Angeles,

CA 90061, telephone (310) 523–2750,

fax (310) 523–2745. 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:

Marc Belhumeur, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Certification Office, Fort

Worth, Texas 76193–0170, telephone

(817) 222–5177, fax (817) 222–5783.

SUPPLEMENTARY INFORMATION: On

November 21, 2000, the FAA issued

Emergency AD 2000–24–51 that applies

to MDHI Model 369A, H, HE, HM, HS,

D, E, FF, and 500N helicopters and

requires, before further flight,

performing a tap inspection on both the

upper and lower surfaces of each blade.

If any voids are detected that exceed

specified inspection requirements, this

AD requires replacing the unairworthy

blade with an airworthy blade before

further flight. That action was prompted

by a blade failure due to fatigue cracking

that originated at corrosion pits on the

spar bonded surfaces, resulting in an

accident that destroyed a Hughes Model

369D helicopter. That condition, if not

corrected, could result in failure of a

blade and subsequent loss of control of

the helicopter.

Since the issuance of that AD, the

FAA discovered an error in the

applicability section. The part numbers

are not listed correctly with the

appropriate serial numbers and, as a

result, the FAA received requests from

operators to clarify which blade part

numbers are affected since the

emergency AD deviates from the

applicable service bulletin. The intent of

Emergency AD 2000–24–51 was not to

deviate from the part numbers and serial

numbers listed in the service bulletin.

To assure affected blades are correctly

identified, the FAA issued superseding

Emergency AD 2000–25–52 to correct

the applicability. The requirements for

accomplishing the intent of the

emergency AD remain the same.

The FAA has reviewed Helicopter

Technology Company, LLC, Mandatory

Service Bulletin No. 2100–2R2, dated

November 14, 2000 (SB), which

describes procedures for performing a

one-time inspection of each blade for

skin-to-spar bonding voids before

further flight.

Since the unsafe condition described

is likely to exist or develop on other

MDHI Model 369A, H, HE, HM, HS, D,

E, FF, and 500N helicopters of the same

type designs, the FAA issued

Emergency AD 2000–25–52 to detect a

void in the bonding that could result in

a crack due to corrosion pits on the

blade spar bonded surfaces, failure of a

blade, and subsequent loss of control of

the helicopter. The AD requires, before

further flight, performing a tap

inspection on both the upper and lower

surfaces of each blade. If any voids are

detected that exceed specified

inspection requirements, this AD

requires replacing the unairworthy

blade with an airworthy blade before

further flight. The actions must be

accomplished in accordance with the

SB described previously. The short

compliance time involved is required

because the previously described

critical unsafe condition can adversely

affect the structural integrity and

controllability of the helicopter.

Therefore, the actions listed previously

are required before further flight, and

this AD must be issued immediately.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

letters issued on December 5, 2000, to

all known U.S. owners and operators of

MDHI Model 369A, H, HE, HM, HS, D,

E, FF, and 500N helicopters. These

conditions still exist, and the AD is

hereby published in the Federal

Register as an amendment to section

39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

The FAA estimates that 300

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 3 work hours per

helicopter to accomplish each

inspection and 5 work hours per

helicopter to replace 1 blade, and that

the average labor rate is $60 per work

hour. Required parts will cost

approximately $10,000 per blade. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $3,630,000, assuming $12,100 per

6452 Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations

helicopter for 10 inspections ($1,800)

and one blade replacement ($10,300).

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available in the Rules

Docket for examination by interested

persons. A report that summarizes each

FAA-public contact concerned with the

substance of this AD will be filed in the

Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their mailed

comments submitted in response to this

rule must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2000–SW–

63–AD.’’ The postcard will be date

stamped and returned to the

commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

2000–25–52 MD Helicopters, Inc.:

Amendment 39–12083. Docket No.

2000–SW–63–AD. Supersedes

Emergency AD 2000–24–51, Docket No.

2000–SW–62–AD.

Applicability: Model 369A, H, HE, HM, HS,

D, E, FF, and 500N helicopters, with main

rotor blade (blade), part number (P/N)

500P2100–BSC (serial number (S/N) with a

prefix of ‘‘K’’ and 101 through 562); P/N

500P2100–101 or P/N 500P2100–301 (S/N

with a prefix of ‘‘A’’ and 001 through 999 or

S/N with a prefix of ‘‘B’’ and 001 through

529); or blade, P/N 500P2300–501 (S/N with

a prefix of ‘‘T’’ and 101 through 107),

manufactured by Helicopter Technology

Company, LLC, 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 (b) 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 before further flight,

unless accomplished previously.

To detect a void in the bonding that could

result in a crack due to corrosion pits on the

blade spar bonded surfaces, failure of a blade,

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Perform a tap inspection on both the

upper and lower surfaces of each blade in

accordance with the ‘‘INSPECTION’’

paragraph of Helicopter Technology

Company, LLC, Mandatory Service Bulletin

Notice No. 2100–2R2, dated November 14,

2000 (SB). If any voids on a blade are

detected that exceed specified inspection

requirements of the SB, replace the

unairworthy blade with an airworthy blade

before further flight.

(b) 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, Rotorcraft

Certification Office, FAA. Operators shall

submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Rotorcraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(c) Special flight permits 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.

(d) The tap inspections shall be

accomplished in accordance with the

‘‘INSPECTION’’ paragraph of Helicopter

Technology Company, LLC, Mandatory

Service Bulletin Notice No. 2100–2R2, dated

November 14, 2000. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Helicopter Technology

Company, LLC, 12923 South Spring St., Los

Angeles, CA 90061, telephone (310) 523–

2750, fax (310) 523–2745. 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.

(e) This amendment becomes effective on

February 6, 2001, to all persons except those

persons to whom it was made immediately

effective by Emergency AD 2000–25–52,

issued December 5, 2000, which contained

the requirements of this amendment.

Issued in Fort Worth, Texas, on January 10,

2001.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 01–1586 Filed 1–19–01; 8:45 am]

BILLING CODE 4910–13–U