Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations 6449

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–391–AD; Amendment

39–12080; AD 2001–01–10]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400, 747–400F, 767–200,

and 767–300 Series Airplanes

Equipped With Pratt & Whitney Model

PW4000 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to all Boeing Model 747–400,

747–400F, 767–200, and 767–300 series

airplanes equipped with Pratt &

Whitney Model PW4000 series engines.

This action requires revising the

Airplane Flight Manual (AFM). This

action is necessary to prevent reduced

acceleration and climb performance

relative to performance data in the

AFM, which could result in runway

overruns or impact with obstacles or

terrain. This action is intended to

address the identified unsafe condition.

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), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

391–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–391–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Dennis Kammers, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2956; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports that Pratt &

Whitney Model PW4000 series engines

with certain early-production fan blades

(Phase 0/1, FB2B or FB2T) installed on

Boeing Model 747–400, 747–400F, 767–

200, and 767–300 series airplanes do

not produce the amount of thrust

indicated in the Airplane Flight Manual

(AFM). This thrust shortfall is due to

erosion of the fan blade’s leading edge.

The flight crew has no indication of this

shortfall in thrust. This condition

results in reduced acceleration and

climb performance relative to

performance data in the AFM, which, if

not corrected, could result in an overrun

of the runway or impact with an

obstacle or terrain.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Telex M–7200–00–02672, dated

November 1, 2000, including two

attachments titled, ‘‘Performance for

Operation of PW4000 Series Engines

with FB2B or FB2T Fans Installed[,]

747–400,’’ and ‘‘Performance for

Operation of PW4000 Series Engines

with FB2B or FB2T Fans Installed[,]

767–200/767–300,’’ both dated

November 1, 2000. The telex and its

attachments contain performance

adjustments for the AFM for Model

747–400, 747–400F, 767–200, and 767–

300 series airplanes equipped with one

or more Pratt & Whitney Model PW4000

series engines with early production fan

blades. Inclusion of these performance

adjustments in the AFM addresses the

unsafe condition associated with the

shortfall in thrust caused by the early

production fan blades.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent reduced acceleration and climb

performance relative to performance

data in the AFM, which could result in

runway overruns or impact with

obstacles or terrain. This AD requires

accomplishment of the actions specified

in the telex and attachments described

previously, except as discussed below.

Differences Between Telex and This AD

Operators should note that, although

the telex states that the airplane

manufacturer was advised that the FAA

would recommend a compliance time of

45 days after the effective date of the AD

for the actions in the telex, paragraph (a)

of this AD actually requires revising the

AFM within 30 days after the effective

date of this AD. In developing an

appropriate compliance time for this

AD, the FAA considered not only the

manufacturer’s recommendation, but

the degree of urgency associated with

addressing the subject unsafe condition,

the average utilization of the affected

fleet, and the time necessary to revise

the AFM. In light of all of these factors,

the FAA finds a 30-day compliance time

for completing the required actions to be

warranted, in that it represents an

appropriate interval of time allowable

for affected airplanes to continue to

operate without compromising safety.

Operators also should note that this

AD applies to all Boeing Model 747–

400, 747–400F, 767–200, and 767–300

series airplanes equipped with Pratt &

Whitney Model PW4000 series engines.

For airplanes that have currentproduction fan blades (Phase 3, FB2C)

installed on all engines, the

performance adjustments in the

attachments to the telex referenced

above are not applicable. However, this

AD requires revision of the AFM for all

airplanes to address the potential for

future installation of early production

fan blades (Phase 0/1, FB2B or FB2T).

Note 1 is included in this AD to clarify

this point.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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 shall identify the

6450 Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations

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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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, both before

and after the closing date for comments,

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 comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–391–AD.’’

The postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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 the following new airworthiness

directive:

2001–01–10 Boeing: Amendment 39–12080.

Docket 2000–NM–391–AD.

Applicability: Model 747–400, 747–400F,

767–200, and 767–300 series airplanes

equipped with Pratt & Whitney Model

PW4000 series engines; certificated in any

category.

Note 1: For airplanes that have currentproduction fan blades (Phase 3, FB2C)

installed on all engines, the performance

adjustments in the attachments to Boeing

Telex M–7200–00–02672, dated November 1,

2000, as referenced in this AD, are not

applicable. However, this AD requires

revising the Airplane Flight Manual (AFM)

for all airplanes to address the potential for

future installation of certain early-production

fan blades (Phase 0/1, FB2B or FB2T).

Note 2: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes 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 (c) 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 reduced acceleration and climb

performance, relative to performance data in

the AFM, which could result in runway

overruns or impact with obstacles or terrain,

accomplish the following:

AFM Revision

(a) Within 30 days after the effective date

of this AD, revise the FAA-approved AFM by

inserting a copy of this AD with Boeing Telex

M–7200–00–02672, dated November 1, 2000,

including the performance adjustments in

‘‘Performance for Operation of PW4000

Series Engines with FB2B or FB2T Fans

Installed[,] 747–400,’’ (for Boeing Model 747–

400 and 747–400F series airplanes) or

‘‘Performance for Operation of PW4000

Series Engines with FB2B or FB2T Fans

Installed[,] 767–200/767–300,’’ (for Boeing

Model 767–200 and –300 series airplanes),

both dated November 1, 2000, as applicable.

(b) When the information in Boeing Telex

M–7200–00–02672 and its attachments have

been incorporated into FAA-approved

general revisions of the AFM, the general

revisions may be incorporated in the AFM,

and this AD with the telex and its

attachments may be removed from the AFM.

Alternative Methods of Compliance

(c) 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, Seattle

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(e) The actions shall be done in accordance

with Boeing Telex M–7200–00–02672,

including Attachments ‘‘Performance for

Operation of PW4000 Series Engines with

FB2B or FB2T Fans Installed[,] 747–400’’ and

‘‘Performance for Operation of PW4000

Series Engines with FB2B or FB2T Fans

Installed[,] 767–200/767–300,’’ dated

November 1, 2000, as applicable. (Note: The

attachment titles are indicated only on the

first page of each attachment; no other page

contains this information.) 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 Boeing

Commercial Airplane Group, P.O. Box 3707,

Seattle, Washington 98124–2207. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

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