Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Rules and Regulations 6455

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–NM–226–AD; Amendment

39–9924; AD 97–03–19]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747

and 767 series airplanes, that currently

requires inspection of the door opening

thrusters and door opening/snubbing

actuators for proper oil quantity, and

modification of the off-wing

compartment latching assemblies. This

amendment adds a requirement for

replacement of the currently installed

door opening thrusters with new,

improved thrusters for Model 747 series

airplanes. This amendment also

removes Model 767 series airplanes

from the applicability of the AD, since

those airplanes are addressed currently

in a separate AD. This amendment is

prompted by reports indicating that the

requirements of the existing AD do not

adequately detect leakage of fluid from

the actuators. The actions specified by

this AD are intended to prevent such

leakage, which could result in failure of

the escape slide to deploy; such failure

could delay and possibly jeopardize the

successful emergency evacuation of an

airplane.

DATES: Effective March 19, 1997.

The incorporation by reference of

Boeing Service Bulletin 747–25–3073,

dated September 21, 1995, as listed in

the regulations, is approved by the

Director of the Federal Register as of

March 19, 1997.

The incorporation by reference of

certain other publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

November 25, 1992 (57 FR 47987,

October 21, 1992).

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207; and OEA

Aerospace Inc., P.O. Box KK, Hwy. 12,

Explosive Technology Road, Fairfield,

California 94533–0659. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 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:

Gregory L. Schneider, Aerospace

Engineer, Airframe Branch, ANM–120S,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2028;

fax (206) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 92–16–17,

amendment 39–8327 (57 FR 47987,

October 21, 1992), which is applicable

to certain Boeing Model 747 and 767

series airplanes, was published in the

Federal Register on June 26, 1996 (61

FR 33050). The action proposed to

continue to require repetitive

inspections of the door opening

thrusters and door opening/snubbing

actuators for proper oil quantity, and

modification of the off-wing

compartment latching assemblies for

Model 747 series airplanes. For those

airplanes, the action proposed to add a

requirement for replacement of existing

door opening thrusters with new,

improved thrusters. Additionally, the

action proposed to remove Model 767

series airplanes from the applicability of

AD 92–16–17, since those airplanes are

addressed currently by AD 95–08–11,

amendment 39–9200 (60 FR 20013).

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

Two commenters support the

proposed rule.

Request To Revise Description of Effect

of Required Actions

One commenter requests that

Summary section of the preamble to the

proposal be revised to replace the word

‘‘preclude’’ with the word ‘‘detect’’ in

the following sentence that appeared in

that section: ‘‘This proposal is prompted

by reports indicating that the

requirements of the existing AD do not

adequately preclude leakage of fluid

from the actuators.’’ The commenter

indicates that the actions required by

AD 95–08–11 do not ‘‘preclude’’ fluid

leakage; rather, they provide a means of

detecting decreased fluid quantities in

an effort to prevent failure of the escape

slide to deploy.

The FAA concurs with the

commenter’s request and justification,

and has revised the Summary section of

this final rule accordingly.

Request To Explain Removal of Certain

Airplanes From Applicability

The same commenter requests that the

Summary section of the preamble to the

proposal be revised to specify that the

new AD action would remove Model

767 series airplanes from the

applicability of AD 92–16–17, since

those airplanes are addressed currently

by AD 95–08–11. The commenter notes

that the existing AD is, in effect, being

superseded by two AD’s, one for each

airplane model. The clarification will

direct operators of Model 767 series

airplanes to the appropriate AD.

The FAA does not consider that

additional clarification is necessary.

This issue was discussed in detail

elsewhere in the preamble to the

proposal. Such detail is unnecessary in

the Summary section to a rule, since

that section is intended to provide only

a synopsis of the proposed or required

actions. Further, since operators of

Model 767 airplanes are no longer

subject to this AD, there is no reason to

address those operators further in this

final rule.

Request To Remove Paragraph (d) From

the Proposal

The Air Transport Association (ATA)

of America, on behalf of one of its

members, requests that the FAA remove

paragraph (d) from the proposal, which

would require that all spare parts be

modified as of the effective date of the

final rule. The ATA states that inclusion

of that paragraph would place an

unnecessary burden on operators of

Model 747 series airplanes. The

commenter points out that AD 95–08–11

provides operators of Model 767 series

airplanes an interval of two years to

modify uninstalled actuators. The ATA

maintains that there is no need to create

different compliance periods between

installed and uninstalled components,

except where results of a risk

assessment support two compliance

periods. The commenter concludes that

proposed paragraph (d) is unnecessary

since paragraph (c) requires that all

airworthy units, installed and

uninstalled, be modified within two

years.

The FAA concurs partially. First, the

FAA does not agree that paragraph (d)

should be removed from this final rule

altogether. The FAA finds that

paragraph (d) must be included in the

AD to ensure that only new, improved

door opening thrusters (that are not

fluid filled) are installed on the affected

airplanes. However, upon

reconsideration of the compliance time

proposed in that paragraph, the FAA

finds that it is appropriate to revise the
6456 Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Rules and Regulations

compliance time for paragraph (d) of

this final rule so that is parallel to a

similar paragraph in AD 95–08–11,

which addresses these same

components for Model 767 series

airplanes. Accordingly, paragraph (d) of

this final rule has been revised to

specify that only new, improved door

opening thrusters shall be installed on

the affected airplanes as of two years

after the effective date of this AD. This

revision will also preclude the potential

for any parts availability problem that

may arise in the interim.

Second, the FAA must clarify for this

commenter that neither paragraph (c)

nor paragraph (d) of this AD address

‘‘uninstalled’’ components. Part 39 of

the Federal Aviation Regulations (14

CFR part 39) precludes AD actions taken

to address components that are not

currently installed on the airplane (or

product). Therefore, the FAA cannot

require via an AD that operators inspect,

repair, or modify a ‘‘spare part’’ (i.e.,

currently in an operator’s parts

inventory). However, the FAA can

ensure, via a requirement such as that

specified in paragraph (d) of this AD,

that any spare part is inspected,

repaired, or modified prior to it being

installed on an airplane. Accordingly,

paragraphs (c) and (d) of this AD do not

require that any action to be taken on

‘‘uninstalled’’ parts (spares). The

requirements of those paragraphs only

specify that, whenever a door opening

thruster is to be installed on an airplane

now or in the future, that thruster must

be an improved model.

Request To Reference Additional

Service Information

One commenter requests that the

proposal be revised to cite the following

service bulletin revisions, which have

been reviewed and approved by the

FAA, as additional sources of

appropriate service information:

• Boeing Service Bulletin 747–25–

3073, Revision 1, dated August 1, 1996.

• Boeing Service Bulletin 747–25–

2951, Revision 1, dated May 13, 1993.

• Boeing Service Bulletin 747–25–

2951, Revision 2, dated September 30,

1993.

• OEA Service Bulletin 2174200–25–

013, Revision 1, dated September 14,

1993.

• OEA Service Bulletin 2174200–25–

013, Revision 2, dated November 1,

1993.

• OEA Service Bulletin 2174200–25–

013, Revision 3, dated January 13, 1994.

The FAA agrees that the service

bulletins listed above, with the

exception of Boeing Service Bulletin

747–25–3073, Revision 1, dated August

1, 1996, should be referenced in the

final rule. The FAA has confirmed that

Boeing has not yet released Revision 1

of Service Bulletin 747–25–3073 due to

changes in the engineering aspects prior

to receipt of FAA approval of that

service bulletin. However, Boeing

advises that it plans to issue Revision 1

of that service bulletin in early 1997

and, subsequently, will request approval

of it as an alternative method of

compliance with this AD.

The FAA has revised the final rule to

add new NOTES 2 and 3, which specify

that accomplishment of the actions

required by this AD in accordance with

the last five service bulletins listed

above is acceptable for compliance with

the requirements of this AD.

Request To Add Address To Obtain

Service Information

One commenter requests that the FAA

revise the Addresses section of the

preamble to the proposal to include the

address for OEA Aerospace Inc., since

an OEA service bulletin is cited in the

proposal.

The FAA concurs. The address for

OEA was omitted inadvertently from the

proposal, but has been included in this

final rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 400 Model

747 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 125 airplanes of U.S.

registry will be affected by this

proposed AD.

The actions that are currently

required by AD 92–16–17 and retained

in this new AD take approximately 12

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts cost approximately

$510 per airplane. Based on these

figures, the cost impact on U.S.

operators of the actions currently

required is estimated to be $153,750, or

$1,230 per airplane.

The new actions that are required by

this new AD will take approximately 2

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $6,400 per airplane.

Based on these figures, the cost impact

on U.S. operators of the new

requirements of this AD is estimated to

be $815,000, or $6,520 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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.

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–8327 (57 FR

47987, October 21, 1992), and by adding
Federal Register / Vol. 62, No. 29 / Wednesday, February 12, 1997 / Rules and Regulations 6457

a new airworthiness directive (AD),

amendment 39–9924, to read as follows:

97–03–19 BOEING: Amendment 39–9924.

Docket 95–NM–226–AD. Supersedes AD

92–16–17, Amendment 39–8327.

Applicability: Model 747–100, –200, and

–300 series airplanes equipped with an offwing, two-piece escape slide on Door 3;

certificated in any category.

Note 1: This AD applies to each airplane

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 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 (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 escape slide to

deploy, which could delay and possibly

jeopardize the successful emergency

evacuation of an airplane, accomplish the

following:

(a) Within 18 months after November 25,

1992 (the effective date of AD92–16–17,

amendment 39–8327), perform an inspection

of the door opening thrusters of the escape

system in accordance with OEA Service

Bulletin 2174200–25–013, dated July 29,

1991. Repeat this inspection thereafter at

intervals not to exceed 20 months until the

replacement required by paragraph (c) of this

AD is accomplished.

Note 2: Inspections accomplished in

accordance with OEA Service Bulletin

2174200–25–013, Revision 1, dated

September 14, 1993; Revision 2, dated

November 1, 1993; or Revision 3, dated

January 13, 1994; are considered acceptable

for compliance with the inspections specified

in paragraph (a) of this AD.

(b) Within 18 months after November 25,

1992, inspect and modify the door latching

mechanism of the escape slide compartment

in accordance with Boeing Service Bulletin

747–25–2951, dated August 15, 1991.

Note 3: Inspections and modifications

accomplished in accordance with Boeing

Service Bulletin 747–25–2951, Revision 1,

dated May 13, 1993; or Revision 2, dated

September 30, 1993; are considered

acceptable for compliance with the

applicable action specified in paragraph (b)

of this AD.

(c) Within 2 years after the effective date

of this AD, replace the door opening thrusters

having part number (P/N) 60B50077–14 or

–17 with new thrusters having P/N

60B50077–19 in accordance with Boeing

Service Bulletin 747–25–3073, dated

September 21, 1995. Accomplishment of this

replacement terminates the repetitive

inspections required by this AD.

(d) As of 2 years after the effective date of

this AD, only door opening thrusters having

P/N 60B50077–19 shall be installed on any

airplane.

(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, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(f) Special flight permits may be issued in

accordance with §§ 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.

(g) The inspections and modification shall

be done in accordance with OEA Service

Bulletin 2174200–25–013, dated July 29,

1991; and Boeing Service Bulletin 747–25–

2951, dated August 15, 1991. The

incorporation by reference of those

documents was approved previously by the

Director of the Federal Register, in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51, as of November 25, 1992 (57 FR

47987, October 21, 1992). The replacement

shall be done in accordance with Boeing

Service Bulletin 747–25–3073, dated

September 21, 1995. The incorporation by

reference of that document 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; and OEA

Aerospace Inc., P.O. Box KK, Hwy. 12,

Explosive Technology Road, Fairfield,

California 94533–0659. 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.

(h) This amendment becomes effective on

March 19, 1997.

Issued in Renton, Washington, on January

31, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3027 Filed 2–11–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–69–AD; Amendment

39–9923; AD 97–03–18]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A, SAAB 340B, and SAAB

2000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A, SAAB 340B, and SAAB 2000

series airplanes, that requires

replacement of the hubcap drive

coupling of the main wheel with an

improved coupling. This amendment is

prompted by reports of unexpected

decreases in the pressure of the main

wheel brake due to incorrect

engagement between the main wheel

coupling and the wheel speed

transducer, which can result in false

signals being sent to the anti-skid

control box. The actions specified by

this AD are intended to prevent loss of

brake effectiveness due to a decrease in

the pressure of the main wheel brake.

DATES: Effective March 19, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 19,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from SAAB Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Transport

Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Walter Eierman, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (310) 627–5336; fax (310)

627–5210.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Saab Model

SAAB SF340A, SAAB 340B, and SAAB

2000 series airplanes was published in

the Federal Register on September 4,

1996 (61 FR 46572). That action

proposed to require replacement of the

hubcap drive coupling of the main

wheel with an improved coupling.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.